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	Back to STI home page   Following are the non-digitized 16mm films comprising the rest of the LaRC collection.   Go back to the digitized films listing. (1) The Sonic Inlet (2) Aerodynamic Noise Test With and Without Engines Running on Landing 16mm, Silent, Color (No. 1) The Sonic Inlet (No.2) Aerodynamic Noise Test with and Without Engines Running on Landing 0.02-Scale X-15 Force Tests; 0.012-Scale X-15 High Angle-of-Attack Force Tests--11 Inch Hypersonic Tunnel 1958 16mm, Silent, Color, 120ft., 3.5min 0.17 Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Color, 225ft., 6.5min. 0.17-Scale Model of Navy Integrated Flight Capsule 1960 16mm, Silent, Black & White, 125ft., 3.5min 0.17-Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Color, 107ft., 3min. 0.17-Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Black & White, 118ft., 3.5min. 0.17-Scale Model of Navy Integrated Flight Capsule, Test No. 2 Wallops Island, VA 1961 16mm, Silent, Color, 90ft., 2.5min. 1/10-Size Model F-86 with Twin Hydro-Skis. Gross Weight, 20,000 Pounds. 16mm, Silent, Color, 60ft., 2.5min. 1/13.33 Scale Model of Preliminary Design Martin XP6M-1 Flying Boat 16mm, Silent, Black & White 1/9-Scale A3J-1 Radio-Controlled Model Spin and Recovery Tests 1960 16mm, Silent, Color, 1475ft., 40min. 1/9-Scale Radio-Controlled A3J-1 Model Parachute Tests 1959 16mm, Silent, Black & White, 100ft., 3min. 1/9-Scale Saturn Model 1960 Originally recorded in 16mm, Silent, Color, 140ft., 5min. 10' P.T. XA-26 Sweep and Dihedral Tests 1943 16mm Sweep and dihedral tests and stall studies of a simplified wing-fuselage combination of a 0.2375 scale model of the Douglas A026 airplane were made in the 19 ft. pressure tunnel. The wing characteristics were; aspect ration 9.08 taper ratio 2.21; root section NACA 652-215 (a=0.8); tip section NACA 652-215 span flap deflected 0-degrees and 55-degrees; aileron drooped 0-degrees and 25-degrees; dynamic pressures 50, 35, and 30lb/aq.ft.; RN's 3.6, 3.1, and 2.8x10 [6th power]; Mach nos. 0.12, 0.10, and 0.09; angles of attack from -4.6-degrees to 15.4-degrees; and lift coefficients from 0.79 to 2.78. Sweep configurations were: normal sweep, 20% chord line straight; sweep forward, -10% chord line straight; and sweep back, 110% chord line straight. 10,000 KVA Heating Facility 1958 16mm, Silent, Color, 585ft., 16min. 116-E Tank 16mm, Silent, Black & White 11-Inch Ceramic Heated Tunnel 16mm, Silent, Black & White, 1400ft., 39min. 131-X with Hydrofoil PB2Y-3 1943 16mm Tank tests of a 1/8 scale dynamic model of PB2Y-3 with a hydrofoil to relieve bow spray by unloading the hull. The span of the hydrofoil is 15.9 in. and the chord is 4.2 in. The full-size conditions are 76,000# gross load, center of gravity of 28% MAC, 1200 BHP/engine, 40-degrees flap deflection, neutral elevators, and acceleration of 1ft/sec./sec. The model was tested without hydrofoil from 0 to 16 fps; with hydrofoil 5.3in. forward of C.G. and 8.2in. forward of C.G.; incidence of 7-degrees and 9-degrees to baseline; gap, hydrofoil to keel, 2/3 and 1 1/4 chords from 0 to 14 and 0 to 16 fps. 133 Tank 16mm 143 E-XP441 16mm, Silent, Black & White 1520 Javelin Payload-Antenna Erection Tests in the Langley 41-Foot Vacuum Sphere-Requested by Goddard Research Center 1961 16mm, Silent, Black & White, 1450ft. 16 Foot Transonic Tunnel Fire (about 1952) 16mm, Silent, Black & White 16-Foot HST Parachute- Schuller; Failure Tests of Parachutes 16mm Strength, failure, and stability tests made in 16ft. high-speed tunnel of 10 parachutes to determine airspeed at which failure occurs. Two different sizes were tested; 7 having a maximum diameter of 38in. and a mouth diameter of 34in., the only difference being in a shroud-line-canopy attachment; and 3 having a mouth diameter of 54in. and identical to each other. 19' Lockheed Wing No. 2 Tufts 1930 16mm Depicts tuft studies made on the Lockheed Wing #2 in the 19-foot pressure tunnel. The tests were made at a density of approximately 70 pounds per square foot; flap deflections of 0%, 25%, 50%, 80%, and 100%, and an angle of attack range from 6-degrees to 20-degrees. 19' P. T. Lockheed Wing No. 1 Tufts 1939 16mm Depicts tuft studies made on the Lockheed Wing # 1 in the 19-foot pressure tunnel. The tests were made at a density of approximately 70 lb. per sq. ft.; flap deflections of 0%, 25%, 50% and 100%; and an angle of attack range from -5-degrees to 20-degrees. 19' P. T. Test 72 1943 Stall studies were made of a semi-span model of the XB-36 airplane in the 19-foot pressure tunnel. The model wing used full span flaps, the in board sections, separated by the nacelles, being the slotted type and the outboard section being of the balanced split type. The tests were run at a Reynolds number of 8,900,00 and a Mach number of 0.17. Tests were run at angles of attack from 12-degrees to 18.6-degree with the flaps not deflected; tests were run at angles of attack from -3.8-dggrees to 18.8 degrees with the inboard flaps deflected 40-degree and the outboard flaps not deflected; tests were run at angles of attack from -3.7degrees to 16.9-degrees with the inboard flaps deflected 40-degrees and the outboard flaps deflected 50-degrees. 19' P.T a-26 Tufts 1943 16mm Stall studies were made, by means of tufts, over the 0.2375-scale model of the Douglas A-26 airplane in the 19ft. pressure tunnel. At flap deflections of 0-degrees, tests were made over a range of angles of attack from 0-degrees to 17-degrees, with the oil cooler duct exits closed then fully opened. At a flap deflection of 55-degrees with oil cooler duct exits closed the angel of attack range was from -7-degrees to 13-degrees. With flaps deflected at 55-degrees and aileron deflected 25-degrees and oil cooler duct exits closed and fully opened, the angle of attack range was from -4-degrees to 8-degrees. Low-drag duct entrance was installed in right wing with exit full open and airplane duct entrance installed in left wing with exit closed and tested over an angle of attack range from 2-degrees to 6-degrees. Oil cooler duct entrances were removed and replaced by filler blocks and tests were made over a range of angles of attack from 4-degrees to 13-degrees. 19' P.T. Pt. III B-32 Testing 16mm Stall tests were made, by means of tufts, were made in the 19 ft. pressure tunnel on a 1/8 scale model of the B-32 equipped with propellers operating at 40% normal rated power for RN approximately 2.6x10 [6th power]. Stall progression is presented for the model, with #4 and #5 nacelle afterbodies tested for various configurations with leading edge gloves and trailing edge extensions, and for double slotted inboard flaps, deflected 40-degrees. Transition was fixed at 10% of the original wing chord. The trailing edge extensions cover 0.6 span. The angles of attack range from 0.1-degree to 15.7-degrees and the lift coefficients range from 0.5 to 2.62. 19' P.T. Tests 112- Part II 16mm Stall studies were made, by means of tufts, in the 19-foot pressure tunnel on a 1/14-scale model of the consolidated B-36 airplane. The model was equipped with midchord slots on the outer wing panels ahead of the ailerons; partial span, single-slotted flaps; and no propeller. RN was approximately 4.5x10 [6th power]; flap deflections were 20-degrees, for the take off, and 40-degrees, for landing; angles of attack range from 0.4-degrees to 19.4-degrees; and lift coefficients ranged from 0.40 to 1.96. 19' P.T. B-32 Testing 16mm, Silent, Black & White Stall tests were made, by means of tufts, in 19 ft. pressure tunnel on 1/8 scale model of the B-32 with propellers operating at 40% normal rated power and RN approximately 2.6x10 [6th power]. Stall progressions are presented for the model, with flaps neutral, testing individually trailing edge extensions, leading edge gloves, and nacelle afterbodies #2 and #3. Combination of the #3 afterbody with trailing edge extensions, cowl flaps at 10-degrees and closed and intercooler flaps closed and open are included. Trailing edge extensions are 1.5 in. wide and cover 30% span. The angles of attack range from 0-degrees to 12.8-degrees and lift coefficients range from 0.08 to 1.16. 19' P.T. B-33 Shield (43"" H/S Test) 19' P.T. B-33 Tufts 16mm Stall studies were made by means of tufts on a 12% model of the B-33 airplane in the 19-foot Pressure tunnel. Tests were run on the normal wing and on the wing with a semi-circular spoiler between the inboard nacelle and fuselage; with rated power, 25% rated power, and with propellers windmilling; with flap deflections of 0-degrees and 40-degrees; with the control surfaces neutral; with R.N.'s of 4.72, 1.68, 3.17, 3.92, 3.84, 1.57, 2.15, 1.91, and 4.64x10 [6th power]; and with angles of attack ranging from 0-degrees to 20-degrees. 19' P.T. B-33 Tufts, Revised 16mm Presents stall studies on the wings of the Martin B-33 by means of tufts in the 19-foot pressure tunnel. The original wing was revised by building in more geometric washout from the outboard nacelle to the tip, thus giving the wing a total geometric washout of 5-degrees. The tests were run on the revised wing with propellers windmilling and with rated power; control surfaces neutral; flap deflection of 0-degree and 40-degrees; R.N.'s of 4.7, 4.01, 1.98, and 1.67x 10 [6th power]; and angles of attack ranging from 0-degrees to 20-degrees 19' P.T. F6F Tufts 16mm Stall studies were made, by means of tufts on a 1/3 simplified scale model of the Grumman F6F airplane with a low-drag wing; modified slotted flaps and dive brakes at the flap deflections 50-degrees and 4-degrees, lip angles 0-degrees and 60-degrees up, RN 5.6x10 [6th power] angles of attack from -4.9-degrees to 16-degrees and lift coefficients from 0.02-1.85. 19' P.T. Test 110-Part II 16mm Stall tuft studies were made in the 19 ft. pressure tunnel on the 1/4 scale model of consolidated B-36 airplane with sharp edge spoilers located on wing leading edge extending from center nacelle to inboard nacelle and from inboard nacelle to fuselage. Tests were made at 40% and full rated power; gross weights 3400,000 lbs. and 265,000 lbs at sea level; RN's 2.45, 2.46, and 2.48x10 [6th power]; inboard flaps deflected 0-degrees, 20-degrees, and 40-degrees, outboard flaps deflected 0-degrees and 50-degrees; angles of attack ranging from -1.6-degrees to 21.7-degrees; and lift coefficients ranging from -0.02 to 2.31. 19' P.T. Test 112- Part 1 1944 16mm Stall studies, by means of tufts, were made in the 19 ft. pressure tunnel on a 1/14 scale model of the consolidated B-36 airplane to determine an acceptable wing configuration. For the tests the propellers were removed and the R.N. was approximately 4.5x10 [6th power]. Tests were made using NACA modified wing outer panel with flaps retracted; double-slotted, partial-span flaps deflected 20-degrees and 50-degrees; from 0.1-degrees to 21.1-degrees; and lift coefficients ranging from .01 to 2.03. Tests were made using CVAC wing outer panel with mid-wing slots; with flaps retracted; single slotted, full-span flaps deflected for take-off (inboard flaps 20-degrees, outboard flaps 50-degrees), landing (inboard flaps 40-degrees, outboard flaps 50-degrees), and 50-degrees; at angles of attack ranging from 0.1-degrees to 21.1; and lift coefficients ranging from .06 to 2.19. 19' P.T. Test No. 110-Part 1 Depicts stall studies of the wing of the Consolidate-Vultee XB-36 airplane in the 19-Foot pressure tunnel. The tests were run with inboard flaps deflected 0-degree and 40-degree; outboard flaps deflected 0-degree and 50-degree; with rated power, 40-percent rated power propellers windmilling, propellers removed; with gross weights at sea level of 265,000 and 340,000 lbs.; with RN's of 2.53, 2.56, 2.6, 5.5, 5.1, and 5.4x10 [6th power] with angle of attach range from -1.5-degree to 21.6-degree; and with lift coefficients ranging from -0.023 to 2.111. 19' P.T. TEST P-36A Tufts 16mm 19' P.T. Tuft Test No. 11 16mm Tuft studies on wings were made in the 19ft. pressure tunnel. 19' P.T. XF14C Tufts 16mm Stall studies of the 0.32 scale model Curtiss F14C-2 airplane were made by means of tufts in the 19 ft. pressure tunnel. Tests were run with propeller off, windmilling, or with a thrust coefficient of 0.06; flaps neutral or down 50-degrees; controls neutral or ailerons drooped 15-degrees; slats open or closed; cowl flap at 0-degrees or 50-degrees; belly flap at 0-degrees or 22-degrees; RN's of 5.7, 5.5, or 5.8x10 [6th power]; and angle of attack range from 0-degrees to 19-degrees. 19' P.T. XF6F Tufts 16mm Stall Studies, by means of tufts, were made of a 1/3 scale simplified model of the Grumman F6F airplane, with a low drag wing, in the 19-ft. pressure tunnel. Tests were made with a short unfaired cannon, long cannon with rounded fairings, 6 gun ports, 6 gun ports and radar fairing with no fillet, and 6 gun ports and radar fairing with small fillet; extensible slotted flaps at 35-degrees. Tests were run at R.N. of 6.15x10 [6th power] and at angles of attack ranging from 8.3degrees to 17-degrees. 19' P.T. XP-67 16mm Tuft studies were made of the McDonnell P-67 full-scale nacelle without power in the 16 ft. high-speed tunnel. General views presented of inboard and outboard duct inlets. Tests made on inboard duct inlet with cooling flap positions fully closed, high speed and fully open at angles of attack 0-degrees, 5-degrees, and 9.5-degrees and indicated airspeeds of 150 and 200 MPH. 19' P.T. XTB2D-1 1944 16mm Stall studies were made in the 19 ft., pressure tunnel on a 0.30 scale semispan model of the Douglas TB2D-1 airplane with endplate seal and fillet and with deflections 30-degrees and 0-degrees; RN's 5.07, 5.06, and 5.32x10 [6th power]; Mach no. 0.12; angle of attack range from -7.9-degrees to 17.3-degrees; and lift coefficient range from-.185 to 2.715. Pull ups are presented on inboard panel from angle of attack 8.1-degrees to 19.3-degrees and on outboard panel from 9.2-degrees to 17.3-degrees. 19' P.T. XTB2D-1 1943 16mm Stall studies were made in the 19-foot pressure tunnel on a model of the Douglas TB2D-1 airplane with endplate seal; fillet off; spoiler on; radar off and on racks off and on; large vane; 2 torpedoes off and on; 4000 lb. bomb off and on; flap deflections 0-degrees and 55-degrees; roll flap deflection 0-degrees to 30-degrees; unmodified 16in. and modified 17 in. oil cooler with maximum and minimum flow; at Mach no. 0.12; RN's of 5.22, 5.27, 5.3, 5.38, and 5.14x10 [6th power]; angles of attack from -5.9 to 16.30-degrees and lift coefficients from -0.188 to -2.615. Pull-ups on inboard panel shown for angles of attack from 9.2-degrees to 14.2-degrees. 19' P.T.Martin Design 195 Tufts 16mm Stall studies, by means of tufts, were made in the 19-ft. pressure tunnel of the 1/6 scale model of the proposed low-drag wing for the Martin design #195 airplane. For all tests, the propellers were windmilling. Tests were made with flaps neutral; NACA slotted flaps deflected 25-degrees and 35-degrees; split flaps deflected 30-degrees and 60-degrees; RN's 4.78, 4.75, 4.85, and 4.87x10[6th power]; Mach nos. 0.18 and 0.17; angles of attack ranging from 2.4-degrees to 21.3-degrees; and lift coefficients ranging from .28 to 2.22. 19' Pressure P. T. P-51 1943 16mm Depicts stall studies made by means of tufts on the North America XP-51 airplane with low drag wing. Tests were made on the wing alone, on the wing and fuselage, and on the wing, fuselage, and fillet. The flap deflection angeles were 0-degrees and 50-degrees; the RN was 5.13x10 [6th power] the angle of attack range was 2.4-degrees to 22.4-degrees; and the lift coefficient range was from 0.27 to 2.06. 19' PT Calibration Tests 16mm, Silent, Black & White 1948 Spin Test 16mm, Silent, Black & White 1956-76 Full Scale Tunnel Free Flight Model (NASA Model) with Leading Edge Devices 16mm, Silent, Black & White 19-Foot Stall Studies of a Simplified F6F With Conv Wing 16mm 24-Inch HST Bomb Fuse AN-M-100 1942 16mm Arming time and functioning tests were made in 24 high-speed tunnel on the Army-Navy M-100 bomb fuse at velocities ranging from 363 to 412 MPH. 24-Inch HST Bomb Fuse M-110 16mm Supplementary arming time and functioning tests were made on bomb fuses WXS-7, 8, 9, 10, 12, 13; WX-20 and 32; 1-M101 and 2-M101 in the 24-inch high-speed tunnel at velocities of 199, 200, 201, 397, 399, and 500 MPH. 24-Inch HST Bomb Fuse M-110, Peco West 16mm Arming time and functioning tests were made in the 24-inch high-speed tunnel on M-110 bomb fuses of the Peco, Westinghouse, and Richard-Westinghouse types at velocities covering a range from 199 through 515 M.P.H. 24-Inch HST Bomb Fuse M-110, Phase 1 16mm Arming time and functioning tests were made of Army M-100, 103, and 110 bomb fuses in the 24-inch high-speed tunnel. Various velocities used covered a range from 103 through 404 M.P.H. 24-Inch HST Bomb Fuse M-110, Phase 2 Arming time and functioning tests were made on the Army M-110 bomb fuse in the 24 High-speed tunnel at velocities of 248, 555, 574, and 573 MPH. 24-Inch HST M-110 Bomb Fuse 1942 16mm Arming time and functioning tests were made in the 24-inch High-speed tunnel on the Army M-100 bomb fuse at velocities ranging from 101-370 M.P.H. 24-Inch HST Radio Masts 16mm Tip deflections of a Naval aircraft radio antenna were measured in the 24' high-speed tunnel at 0-degrees and airspeeds from 100 to 600 MPH. 4-Foot SSPT Schileren 1949 Conference 16mm, 290ft., 16min. 8' HST P-47 Flutter 1942 16mm Flutter tests on P-47 fin-rudder unit were made in the 8-foot high-speed tunnel over an approximately true tunnel speed range from 200 to 460 M.P.H. Failure occurred at approximately 468 M.P.H. (410 M.P.H. indicated). 8' HST P-47 Flutter-Second Test 16mm Flutter tests of the Republic P-47 fin-rudder unit wee made in the 8-foot high-speed tunnel. 8' HST P-47 Metal Rudder Flutter 16mm Flutter tests of the Republic P-47 rudder were made in the 8-foot high-speed tunnel. 9x6 Panel Flutter Tests 1959 16mm, Silent, Black & White, 180ft., 5min. 9x6-Foot Thermal Structures Tunnel 1958 16mm, Silent, Color, 385ft., 11min. A Demonstration of Computer-Aided Structural Design 1968 16mm, Sound, Color, 221ft., 6.6min. A Group of High Speed Configuration Take-Offs and Landings 16mm, Silent, Color, 400ft., 16min. A Study of Ditching 16mm, Silent, Black & White The Army and Navy requested the NACA to investigate the behavior of military air planes while ditching in order to obtain information that would help reduce the loss of personnel in that operation. The only feasible method appeared to be the ditching of dynamically similar scale models of the airplanes. Although their was uncertainty as to exactly how accurately the behaviors of the models reproduced those of the full-size airplane, the comparative results gave useful information. Failure of a part of the full-size airplane is simulated by removing the corresponding part of the model before ditching. The models tested were the SB2C-1, B-17, B-32, B-24, B-25, and B-29. Tests were made in Tank # 2 and using the seaway catapult. Most of the models dived when ditched, but than can be prevented by the use of a hydroflap, hydrofoil, or hydrospoiler under the nose or by reinforcement of the bomb-bay doors to prevent their failure when ditching. Through the cooperation of the Army Air Forces, it was possible to ditch and Actual B-24 under controlled conditions. The airplane was ditched in the James River. Despite extensive reinforcement the airplane was damaged severely. From the comparison of the ditching of the full-size B-24 with the tests of models it was concluded that tests of model give very good approximations of the behavior of the full-size airplanes. A Study of Low-Speed Flight Characteristics of Powered Lift Jet Transports 1965 16mm, Sound, Color, 670ft.,19min. A Study of the Flow Over Several Thick Symmetrical Airfoils. 16mm, Silent, Black & White, 690ft., 28min. A Study of the Use of Canard Surfaces as an Aid in Recovering from Spins and Preventing Directional Divergence Near the Stall Film 1955 16mm, Silent, Black & White A Technique for Determining Wake Location from a Helicopter in Flight 1961 Originally recorded in 16mm, Silent, Color, 660ft., 15min. A Visual Aid for Determing the Characteristics of Gases Vented Into a Supersonic Stream 1961 16mm, Silent, Black & White, 285ft., 7min. A Water Immersion Technique for Zero Gravity Simulation of Astronaut Ingress-Egress Maneuvers 1965 16mm, Silent, Black & White, 290ft., 8min. A Wind Tunnel Guest Response Technique 1965 16mm, Sound, Color, 170ft., 4.5min A-26 16mm, Silent, Black & White, 253ft. A-57 H/S Ejection Test and OFO/RMS Payload: Part II- A-47 H/S 16mm, Silent, Black & White Abalation Tests in 700-kw Arc Jet. 1961 16mm, Silent, Black & White, 120ft., 3min. ABMA 20 MC Antenna Release Tests in 41-Foot Sphere 1959 16mm, Silent, Black and White, 6000ft., 2hr. 49min. ABMA Jupiter Nose Cone Advanced Materials Evaluation Program 1960 16mm., Silent, Black & White, 300ft., 9min. ABMA Payload 16 Antenna Release Test 1959 16mm, Silent, Black & White, 3160ft., 88min. A-Bomb (Print) 16mm, Silent, Black & White News of the day presents Atom Bomb Blast No.5. World's most astounding man-made phenomenon filmed by cameramen of U.S. Navy, Coast Guard, Army Air Forces and American newsreels of underwater explosion of the atomic bomb during Operations Crossroads in the Bikini Lagoon. Access 16mm, Silent, Color Aces, Washington Show 1964 165mm, Sound, Color Acoustic Exposure Tests for Squirrel Monkeys 16mm, Silent, Color, 420ft., 11.6min. Advanced Composite Aileron 1968 16mm, Sound, Color 13min. Advanced Composite Elevator for the Boeing 727 Aircraft 1981 16mm, Sound, Color, 14min. Advanced Composite Vertical Fin Component for L-1011 Aircraft 1984 16mm, Sound, Color 11min. Advanced Composite Vertical Fin-Manufacturing 1982 16mm, Sound, Color, 600ft. Advanced Composite Vertical Fin-Quality Assurance 1982 16mm, Sound, Color, 400ft. Aerodynamic and Deployment Characteristics of Multistage Canopy and Suspension Line Reefing System for a Twin Keel All Flexible Parawing. 1970 16mm, Silent, Color, 120ft., 3.5min. Aerodynamic and Flow Visualization Studies of Two Delta Wing Entry Vehicles at a Mach Number of 20.3 1973 16mm, Silent, Color, 5min. Aerodynamic and Hydrodynamic Characteristics of Models of Some Aircraft-Towed Mine Sweeping Devices 16mm, Silent, Black & White, 465ft, 13min Aerodynamic Characteristics of Parachutes at Mach Numbers from 1.6 to 3 1961 Originally recorded in16mm, Silent, Black & White, 1000ft., 28min. Aerodynamic Characteristics of the X-15/b-52 Combination 16mm, Silent, Black & White, 641ft., 18min. Carry loads, aerodynamic interference effects and drop characteristics of x-15 through b-52 flow field Aerodynamic Drag and Stability Characteristics Towed Inflatable Decelerators at Supersonic Speeds 1962 16mm, Silent, Black & White, 90ft., 2.5min. Aerodynamic Heating and Deceleration During Entry Into Planetary Atmospheres 1962 Originally recorded in 16mm, Silent, Black & White, 1100ft., 29min. Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers up to 14 1958 Originally recorded in 16mm, Silent, Black & White 330ft., 9min. Aerodynamic Research Relative to Variable Sweep Aircraft 1961 16mm, Silent, Color, 275ft., 7.5min. Aeroelastic Phenomena and Research Techniques 1972 16mm, Silent, Color, 11min. Aeroelastic Tests of an Eight Percent Scale Saturn C-1 Block II 1963 16mm, Sound, Color, 188ft., 5.25min. Aeroplastic Phenomena and Related Research 1973 16mm, Sound, color, 482ft., 13.5min. AIR AND SPACE (For Paris Air Show) 1977 16mm, Silent, Color Air Cushion Landing Gear 1966 16mm, Silent, Color Air Cushion Landing Gear 1966 Air Force Day Film--194819' P. T. P-51, 194019' Rough Water Landings of a 1/8-Scale Model of a Grumman JRF-5 with and without Hydro-Skis (Model Film Data, Dec. 1948) 1948 16mm, Silent, Black & White, 90ft, 4min Air Force Movie--Goose with Skis 16mm Air to Air Tracking Using an APQ-35B Radar System 16mm, Silent, Black & White/Color Aircraft Crash Tests Composite Data Film 'A' Wind 1978 16mm, Silent, Color, 788ft., 22min. Aircraft Structural Testing in True Temperature Supersonic Jets 1956 16mm, Silent, Color, 120ft., 3min. Aircraft Trailing Vortices 1970 16mm, Silent, Color, 430ft., 12min. Aircrafts 16mm, Silent, Color Air-Flow Characteristics on a 40-Degree Sweptback Wing as Indicated by Surface Tufts. 1957 16mm, Silent, Black & White, 100ft., 3min. Air-Flow Visualization for Several Rotor Configuration Models Operating in the Static Thrust Condition 16mm, Silent, Black and White, 210ft., 9min. Airline Pilot Visual Scanning Studies Conducted Jointly by NASA LRC/AMES at Piedmont Airline Training Facility 1977 16mm, Sound, Black & White, 270ft., 7.5min Ames Laboratory 6'x6' Wind Tunnel 16mm, Color, 376ft. Construction and operation of the 6-foot by 6-foot supersonic tunnel at Ames Aeronautical Laboratory are presented. Several views of the power plant which furnishes power for the operation of this tunnel are also shown. Ames Laboratory in Action 16mm This is a publicity film showing aerial views of Langley, Aeronautical Laboratory, Lewis flight Propulsion Laboratory, and Ames Aeronautical Laboratory. Since the film was made by and for AAL, views of AAL laboratory and its activities are presented, including views of AAL Sheet Metal Shop, views of various wind tunnels and tests carried on in them. Actual views, schematic diagrams, and tests are shown in the 40x80-foot, the two 7x10-foot, the 16-foot high-speed, the 12-foot pressure tow-turbulence, and the 1x3-foot tunnels. An ice prevention test on and airfoil was made by mounting an airfoil on top of a C-47 in flight, and the wing flow test was made on a model mounted on the wing of a P-51 in flight. Full-scale airplanes are P-512, P-39, C-47, P-80, and F4F. Instruments, designed and assembled by personnel at AAL, are also presented. An Advanced Composite Stabilizer for the Boeing-737 1982 16mm, Sound, Color, 6min. An Energy Absorption Process Employing Frangible Metal Tubing 1964 16mm, Sound, Color, 290ft., 8min. An Evaluation of Linearized Vortex Theory as Applied to Single and Multiple Rotors Hovering In and Out of Ground Effect 1959 16mm, Silent, Black & White, 190ft., 5min. An Experimental Study of the Effect of Downwash from a Twin Propeller VTOL Aircraft on Several Types of Ground Surfaces 1962 16mm, Silent, Color, 670ft., 18.5min. An Exploratory Investigation of Jet Blast Effects on a Dust Covered Surface at Low Ambient Pressure 1961 Originally recorded in16mm, Silent, Black & White, 702ft., 19.5min. An Investigation of Resonant, Nonplanar Free-Surface Oscillations of a Fluid 1962 16mm, Sound, Color, 275ft., 7.5min. An Investigation to Determine the Effect of Lithium Hydride as an Internal Coolant in Stainless Steel and Molybdenum Models 1961 16mm, Silent, Color, 965ft., 27min. Animation and 30 Cell Manometer Records for Ames Conference. 1950 1950 16mm Apollo 13 Review Board Test Support Operations 16mm, Silent, Color, 8min. Apollo-Lunar Orbital Rendezvous Technique Originally recorded in 16mm, Sound, Color, 219ft., 5min. Apollo-Soyuz 1975 Apparatus for Study of Electomagnetic Wake Propagation Through an Ionized Gas 1958 16mm, Silent, Color, 140ft., 4min. Arial of Scout 16mm, Silent, Black & White Assembling and Testing of the Parachute Recovery System for the Temco Corvus Missile at Wallops Island, VA 16mm, Silent, Color, 15.5min. Assembling and Testing of the Parachute Recovery System for the Temco Corvus Missile at Wallops Island, Va. 1958 16mm, Silent, Color, 560ft., 15.5min. AST Structural Panel Program Weldbrazed Panels 8-5-74 1974 16mm, Sound, Color, 400ft., 10min. Astronaut Personality Clips (John Young STS-1 Pilot) 16mm, Silent, Color Astronaut Shepard Reports on Space 1962 16mm, Sound, Color, 720ft., 20min. Atlas Missile Test Project 16mm, Silent, Color Automobile Dual Braking 1967 16mm, Sound, Color, 432ft., 12min. AWT XPB2M-1 Flutter 16mm B-17 Training Film Catapult 16mm Catapult tests were made, using the seaway catapult at Langley Field, VA., to determine the ditching performance of the Army B-17F airplane. For the tests a 1/16 scale dynamic wooden model was used. The flaps were semi-fixed in the down position. Representative power-off landings were made from high, medium, and low altitudes, at angles of attack of 3 1/2-degrees, 7-degrees, and 10-degrees and airspeeds of 98, 110, and 122 MPH, in smooth water, across the waves and along the waves for the complete model and for the model in a damaged condition in which failure of the nose window, bomb-bay doors, camera hatch, lower turret, rear entrance door, tail wheel well, and rear gunner's entrance door simulate. Two three-wheel landings at angle of attack of 0-degrees and 135 MPH airspeed are also shown. Smooth water tests were made with the bomb-bay doors and gun turret in position and hydroflap installed to increase the landing run and to keep the nose clear. B-19 1/20 Model Ditching Tests (Part II Rough) 16mm, Silent, Black & White Ditching tests were made by using the seaway catapult at Langley Field, VA., on a 1/20-scale model of the Army B-29 airplane in rough water. Scale strength flaps were used and all values; weight of 105,000 lbs., C.G. at 25% MAC and 32 in. above the fuselage center line; attitude angles of 1-degree and 9-degree, flap deflections of 45-degree and airspeeds of 104 and 128 MPH; refer to the full-scale airplane. Rough water tests were made with nose window, nose wheel door, main wheel doors, bomb-bay doors, section of fuselage between the bomb-bay doors, camera hatch, main entrance door, and tail skid door removed to simulate their failure. Runs were made with wave crests parallel and perpendicular to flight path in waves from 5-12 feet high. Landings were made with one wing low and initial contract on crest and on windward side of wave. B-24 Army Training Film Catapult 16mm, Silent, Black & White Catapult tests were made, using the seaway catapult at Langley Field, VA., to determine the ditching performance of the army B-24 airplane. A 1/16-scale dynamic wooden model was used with various structural parts, as the bomb-bay doors, nose-wheel doors, and entrance hatches removed to simulate a damaged condition, and C.G. at 28.5% MAC. Representative power off landings were made with the flaps down in smooth water, across waves, and along waves, for light and heavy weight conditions, in tail down, 2-wheel and 3-wheel landing attitudes. The first series of runs were made with the bomb-bays removed and complete bulkhead behind the bomb-bay. The last series were made with bomb-bay doors partially retracted so that only the flat portion of the fuselage was open. B-24 Ditching Instrumentation 16mm B-24 Ditching with Hydro-Scoop 16mm, Silent, Black & White A method considered for improving the water performance of land planes during ditching requires a hydro-scoop to be installed on the rear part of the fuselage. To determine the full-scale hydrodynamic characteristics of a hydro-scoop, one was installed on a B-24 airplane which was ditched at the AAF Proving Ground Command at Eglin Field, Florida. The experiment was made cooperatively by the NACA; which developed, designed, and built the instrument; and the AAF. A NACA photo-observer incorporating instruments to record airspeed, attitude and longitudinal deceleration was a part of the instrumentation. Eight gun-sight cameras were equipped with special wide -angle lenses and installed in waterproof housings. The B-24 was flown to the ditching site by radio control from the C-45 mother plane. It had been planned to land the airplane on the water at a high (near stall) attitude with a low forward speed. However, due to the pilot's inability to judge the airplane's altitude, it contacted the water at a 1-degree nose-down attitude, with a speed of 107 MPH, and a rate of descent of 9 fps. Because of the temporary failure of the instrument radio switch, the photo-observer and damage cameras did not start recording until 1 second after impact, at which time the damage cameras were submerged, and the record of the damage occurring during ditching had to be obtained from observation by divers. The airplane was severely damaged, leaving a stream of debris in its wake, and sank within 6 minutes. Since the hydro-scoop was designed to be effective in a high-attitude landing, the experiment did not give and evaluation of the effectiveness of the hydro-scoop as a ditching aid. Graphs of attitude and deceleration showing the time-history of the airplane during the ditching run are presented. The airplane ran only 3 lengths after contacting the water, and had a maximum deceleration of 4 G, which occurred immediately after contact. B-24 Tufts 19' P.T. 16mm, Silent, Black & White B-24 Wheel Pictures 16mm Presents a flight investigation of the effects of landing impact on horizontal tail loads. Landings were made with the main wheels in one of 3 positions; (1) initially stationary but free to rotate, (2) prerotated, (3) locked with brakes. Landings were made at ground speeds of 96, 101, 103, 107, 114, and 122 MPH; at vertical velocities of 2.1, 2.2, 4.0, 4.2, 6.7, and 6.9 FPS; at attitude angles of -0.0, 3.2, 2.9, and 4.8-degrees; normal accelerations 0.6g, 0.8g, 1.05g, 1.12, and 1.55g. The landing gear frequency and frequency of the horizontal tail in symmetrical bendings are substantially the same about 7 cycles/sec. Occasionally both main wheels touch at these same time and the fore-and-aft oscillations are in phase. When this happens the tail approaches resonance with the landing gear, and tail vibrations of increasing amplitude occur, although the amplitudes of the landing gear oscillations are decreasing. Tail loads are greatly reduced when the wheel oscillations are eliminated by pre-rotation or braking. B-32 Airplane 19 Foot Pressure Tunnel Test 109 16mm, Silent, Black & White B-32 Part 4-- Tufts 19' P.T. 16mm, Silent, Black & White B-32 Part IV Tufts 19' P.T. 16mm Stall tests were made, by means of tufts, in the 19 ft. pressure tunnel on a 1/8 scale of the B-32 at an RN approximately 2.6x10 [6th power]. Stall progression for the model is presented with propellers operating at 40% normal rated power windmilling, and off; with various configurations - leading edge gloves and 60% span trailing edge extensions added, cowl flaps open10-degrees and closed, intercooler flaps open and closed, standard nacelles, nacelle afterbodies #3 and #4 - at flap deflections of 0-degrees and 40-degrees, angle of attack range from 0-degrees to 12.9-degrees, and lift coefficient range from 0.05 to 2.57. Transition was fixed at 10% of the original wing. B-32 Testing 16mm Stall Tests were made, by means of tufts, in the 19-foot pressure tunnel on a 1/8 scale model of the B-32 with propellers operating at 40% normal rated power; RN configuration, with transition fixed, through the range of flap deflection of 0-degrees, 10-degrees, 20-degrees, 30-degrees, and 40-degrees; and with the cowl flaps at 10-degrees or closed and intercooler laps closed and open. Natural transition in the clean condition is included for flap deflection of 0-degree, angle of attack range from 4.3 degrees to 11.8-degrees and loft coefficient range from 0.47 to 1.20. For the tests with transition fixed the angles of attack ranged from 0-degrees to 14.7-degrees and the lift coefficients ranged from 0.7 to 2.57. B-35 Test 127 16mm, Silent, Black & White Stall tests were made, by means of tufts, were made in the 19ft., pressure tunnel on a 1/8-scale model of the B-32 equipped with propellers operating at 40% normal rated power for RN approximately 2.6x10[6th power]. Stall progression is presented for the model, with 34 and 35 nacelle afterbodies tested for various configurations with leading edge gloves and trailing edge extensions, and for double slotted inboard flaps, deflected 40-degrees. Transition was fixed at 10% of the original wing chord. The trailing edge extensions cover 0.6 span. the angles of attack range from 0.1-degree to 15.7-degree and the lift coefficients range from 0.50 to 2.62. B-36 (Revised) Outboard Nacelle 16mm, Silent, Black & White Stall studies were made by means of tufts in the pressure, low-turbulence tunnel on the revised 1/4-scale model of the outboard nacelle of the B-36 airplane at RN of 1.68x10 [6th power] over a lift coefficient range from 0.49 to 0.943. Rear top view of the nacelle and three-quarter front view of the air inlets are shown. Ball Spring, Etc.--Rhode 16mm Beating the Heat 1957 16mm, Sound, Color, 650ft., 19min Bell Multi-Skin Tests in Wallops Island High Temperature Jet 16mm, Silent, Color, 380ft., 10.5min. Bell-Raytheon Structural Integrity Test of a Composite Panel Consisting of: 0.03-Inch Degassed Astrolite Sheet, 3/8-Inch-Thick Ectofoam Insulation 1/16-Inch-Thick Aluminum 1959 16mm, Silent, Black & White, 255ft., 7min. Beryllium Hemispherical Nose Models Supplied by Lockheed Aircraft Corp. for U.S. Navy Polaris Program 1958 16mm, Silent, Black & White Big Shot Viewing Test No. 6, August 24, 1961 1961 Originally recorded in 16mm, Silent, Black & White, 340ft., 9.5min. Blast Effects of Twin Variable-Cant Rocket Nozzles on Visibility During Landing on a Particle-Covered Surfaces 1964 Originally recorded in 16mm, Silent, Black and White, 1655ft., 1hr. 46min. Body Vapor Screen Tests Langley 4- by 4-foot Supersonic Pressure Tunnel. M=20 16mm, Silent, Black & White, 410ft, 17min Boeing Dyna-Soar in Unitary 1959 16mm, Silent Boeing Dyna-Soar in Unitary 16mm, Silent, Black & White Boeing Dyna-Soar In Unitary 16mm, Silent, Black & White Boeing Dyna-Soar Project. I.N. 59-187; I.N. 59-218 1959 16mm, Silent, Black & White, Boeing Dyna-Soar Tests in the Langley 11-Inch Hypersonic Tunnel 1961 16mm, Silent, Color, 140ft., 4min. Boeing Model 1 E 1957 16mm, Silent, Black & White, 225ft., 6min. Bomb Fuses 1942 A number of tests on bomb fuses were shown. 16mm Bomb Releases at Supersonic Speeds 16mm, Silent, Black & White Boron Composites in the CH 54B Helicopter 1972 16mm, Sound, Color, 500ft., 14min. Boron-Epoxy Reinforced C-130 Center Wing Box Program 1975 16mm, Sound, Color, 21min. Boy Scouts--First in Space 16mm, Sound, Color, 400ft., 11min. Buckling Strength - Curved - Combined Compression and Shear 16mm Bureau of Aero. Design #22A DR Model # 206 16mm, Silent, Black & White Landing tests and spray characteristics tests on bow, in propellers, on flaps and on tail surfaces of a 1/11-scale dynamic model of the Bureau of Aeronautics design #22ADR, class VPB airplane were made in Tank #1. For the spray characteristics tests the model was tested with gross loads of 78.1, 93.0, 107.9 and 122.7lbs.; with flaps deflected 20-degrees; stabilizers deflected -9.5-degrees to wing; C.G. at 28% MAC; and full power. As the weight of the model increased the spray remained in the propellers for increasing distances during accelerated runs. For the Landing tests the flaps were deflected 20-degrees, stabilizers deflected -9.5-degrees to wing, C.G. at 38% MAC, ? static thrust was used and the gross loads were 78.1 and 93.0lbs. The trim angles covered a range from 14.1-degrees to 4-degrees. Burning of Metal Rods in a Supersonic Jet 16mm, Silent, Color, 60ft, 2.5min Cable Splice and Spreader Arm Assembly 16mm Calm and Rough Water Ditching Investigation of a 0.043 Scale Model of a Typical Jet Transport With and Without Ditching Aids 1058 15mm, Silent, Black & White, 201ft., 5.5min. Calm and Rough Water Ditching Investigation of a 0.043 Scale Model of a Typical Jet Transport with Landing Gear Extended 1957 16mm, Silent, Black & White, 220ft., 6min. Cambridge Research Center Sounding Rocket Test at Wallops Island, Virginia 16mm, 365ft., 10min. Candidate Space Shuttle Orbiters M+20 Electron Beam Flow Studies, Long Version 1970 16mm, Silent, Color, Candidate Space Shuttle Orbiters M=20 Electron Beam Flow Studies Dec. 1969 Short Version 1969 16mm, Silent, color, 210ft., 6min. Cargo Transfer in Rough Water - Part-1 16mm, Silent, Black & White, 400ft., 16min. Carrier Landings 16mm, Silent, Black & White Catapult Ditching B-25 16mm, Silent, Black & White Ditching tests were made using the seaway catapult at Langley Field, VA., on a 1/11 scale dynamic model of the Army B-25 airplane in heavy weight condition and a no bomb-load, partial fuel-load condition; with flaps semi-fixed in the full-down position; Bombardier's window, the three-wheel doors, the entrance hatches, and the bomb-bay doors omitted. High and medium attitude landings were made in smooth water; across wind, along wave; and into wind, across waves; at airspeeds ranging from 86 to 105 MPH, weights of 22,600 and 25,800 lbs., and attitude angles ranging from 6-degrees to 13-degrees. Catapult Ditching Tests of A-26 Part 4 16mm Ditching tests were made using the seaway catapult at Langley Field, VA. on a 1/12 scale model of the Army A-26 airplane in calm and rough water. All values weight of 25, 730 lbs., C.G. at 28.4% MAC and 5.1 in. above thrust line, flaps deflected 55-degrees, attitude angle of 8-degrees, airspeed of 100 MPH; refer to the full-scale airplane. Tests were made with the nose-wheel doors, bomb-bay doors, main landing gear doors, aft end of the nacelles, and lower turret-service door removed to simulate their failure; with all-purpose nose door closed and braced open 30-degrees to the thrust in to form a hydro flap; in calm water, parallel to 2 and 3 ft. waves perpendicular to 2, 3, and 6ft. waves; at ground speeds from 68 to 122 MPH. Celestial Mechanics and the Lunar Probe 1958 16mm, Sound, Color, 327ft., 10.5min. Centrifugal Antenna Erection 1961 16mm, Silent, Black & White, 2788ft., 1hr. 22min. Ceramic Heat Exchanger 1956 16mm, Silent, Color, 280ft., 8min. Circulation in Drops 16mm, Silent, Black & White Classroom In Space-The Getaway Special 16mm, Sound, Color Cold Separation Test for the S-55B, February 1962 1962 16mm, Silent, Black & White, 910ft., 25min. Color Schlieren Motion Picture of a Cascade of 65-(4A10)06 Blade Section in Reverse in the Langley 7-Inch High Speed 1956 16mm, Silent, Color, 150ft., 4min. Combat Traction--USAF-NASA Cooperative Project 1970 16mm, Silent, Color, 320ft., 9min. Comparative Measurements of Man's Walking and in Earth and Simulated Lunar Gravity 1966 16mm, Silent, Color, 70ft., 2min. Comparison and Evaluation of Several Chemicals as Agents for Rocket-Vehicle Production of Smoke Trails for Wind-Shear Measurements. 1964 16mm, Silent, Color, 790ft., 22min. Comparison Film Skate 7 With and Without Skies 16mm Comparison Of Wind Tunnel And Flight Vortex Systems 20 Degrees Angle Of Attack 16mm, 5.53min Completely Flexible Wings With Variable Geometry 1967 16mm, Silent, Color, 130ft., 3.5min. Compressibility 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 1969 16mm, Silent, Black & White, 205ft., 5.6min. Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Spiral Galaxies 16mm, Silent, Black & White Computer Simulation of Spiral Galaxies 16mm, Silent, Black & White Computerized Circuit Analysis With Visual Input/Output 16mm, Silent, Color Computers in Aerospace Research 1964 16mm, Sound, Color, 875ft., 24min. Conference at LAL- Univ. Professors 1948 16mm, Silent Pictures were made at the University Conference on Aerodynamics of professors who came to LAL from all over the U.S. to be brought up to date on all phases of aerodynamics. Pictures were made in the 7 by 10-foot tunnel building and on the lawn of the recreation building in the West Area Consolidated--Vultee XP-92 Nose Capsule Release, Report No. 25 Consolidated--Vultee XP-92 Report No. 50 Construction of Wooden Propellers 16mm The entire process through which sitka spruce passes to become a 45ft. wind tunnel propeller is depicted. The NACA, through refusal of propeller manufacturers to make these propellers, was forced to set up a shop and train model makers to do the job. Shows special tools developed by NACA to be used on the propellers in various phases of the construction process. Control Missile John Hopkins 16mm, Silent, Black & White At the request of the Bureau of Ordnance, Navy Department, roll stabilization tests of the Johns Hopkins CTV control missile were conducted in the high speed 7' x 10' tunnel in order to obtain information concerning the roll stabilization systems employed. Motion picture records were taken during the tests at the same time the missile and aileron motions were being recorded by electrical methods. Tests were made with follow up ratios of 6/1, 4/1, 2.5/1, and 1.6/1; feed back of 100% and 200%; rate gyro at 100%, 50%, and 0; at velocities from 355 to 503 MPH; and Mach nos. from 0.483 to 0.699. Controlled Tethering in Space 1965 16mm, Sound, Color, 600ft., 16.5min. Convair B58A Model in Langley 4-Foot SPT for Test No. 233 1960 16mm, Silent, Color, 85ft., 2.5min. Convection and Radiation Heating Apparatus 1952 16mm, Silent, Color Copy Scout Test Vehicle 16mm, Silent, Color Correlation of the Ditching Performances of a 1/16-Size Dynamic Model of the Army B-24 Airplane and the Full Size Airplane 1958 16mm, Silent, Black & White, 170ft., 7min. Countersunk Rivets 16mm Presents a comparison of tightness of joints constructed by the use of 3 classes of machine-countersunk rivets for aircraft. Those of class 1 have an annular gap around the rived head caused when the hole is countersunk to a depth greater than the height of the rivet head. The height of the heads of rivets in class 2 is equal to the depth of the hole, thus forming no gap and increasing the tightness of the connection. Rivets of class 3 are those whose heads protrude above the surface. These are the tightest rivets when preformed countersunk heads are used. A still tighter flush rivet can be obtained by inserting a round-head rivet from the back and forming the countersunk head by driving. For the 2 tightest rivets, the heads protrude above the skin surface after driving. The protruding portion of the heads is removed by a flush-rivet milling tool, which may be set to shave off the heads very close to the surface. Desirable aerodynamic smoothness is obtained by painting or polishing the surface. Crash Tests of Four Identical High-Wing Single-Engine Airplanes 16mm, Silent, Color, 15.5min. Crew Motion Disturbances- Simulation of Determination of Vehicle Disturbance Due to Crew Activity 1967 16mm, Silent, Color, 310ft., 8.5min. Cutting-005in. Slots for Laminar Flow Control Airfoil 1977 16mm, Silent, Color, 145ft., 4min. Data Film on the 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane--Part II 1955 16mm, Silent, Black & White, 905ft, 37min Data From a Static-Thrust Investigation of a Large-Scale General Research VTOL-STOL Model in Ground Effect. 1960 16mm, Silent, Color, 315ft., 8.5min. The model was tested at two different elevations with the wing pivot at 1.008 and 2.425 propeller diameters above the ground. The slipstream of the propellers was deflected by tilting the wing and propellers, by deflections of large-chord trailing-edge flaps, and by combinations of flap deflection and wing tilt. Tests were conducted over a range of propeller disk loadings from 7.41 to 29.70 pounds per square foot. Force data for the complete model and pressure distributions for the wing and flaps behind one propeller were recorded and are presented in tabular form without analysis. DC-3Tufts in Flight Presents tuft studies over wings and ailerons of Douglas DC-3 in Flight 16mm Deck Inlet and Planning Tail Configurations 16mm, Silent, Black & White, 185ft, 7.5min Deep Sea Diving 1961 Originally recorded in 16mm, Silent, Black & White, 800ft., 22min. Delta-Wing Hydro-Ski Configuration 16mm, Silent, Black & White, 100ft., 4min. Demonstration of Fuel Sloshing in a Sphere-1st. and 2nd. Modes 1959 16mm, Silent, Color, 125ft., 3.5min. Demonstration of In-Flight Variation of Wing Sweep With a 1/10-Scale Free Flying Model of a Variable Sweep Attack Airplane 1961 16mm, Silent, Color, 93ft., 3min. Demonstration of Structural Feed-Back Instability 1959 15mm, silent, Color 70ft., 2min. Deployment and Performance Characteristics of 5-Foot Diameter (1.5m) Attached Inflatable Decelerators from Mach Numbers 2.2-4.4 1970 Originally recorded in 16mm, Silent, Color, 160ft., 4.5min. Deployment and Stability of Flexible Gliders 1960 16mm, Silent, Black & White, 360ft., 10min. Deployment Tests of the Stratos-Western Version of the Integrated Aircrew Escape/Rescue Capability (AERCAB) System in the Langley Full Scale Tunnel 1970 16mm, Silent, Black & White, 1010ft., 28min. Deployment Tests of Jinivik Air Cushion Recovery and Take Off Systems at High Forward Speeds 1977 16mm, Silent, Color, 1200ft., 28min. Development of a Towed-Model Flutter Test Technique in the Langley 19' Pressure Tunnel 16mm, Silent, Black & White Development of Ventilation on a Surface Piercing Hydrofoil 1958 16mm, Silent, Color, 100ft., 3min. Device Designed and Constructed at Langley Research Center Undergoing an Ejection and Inflation Test in the 5-by-10 Foot Vacuum Chamber. 1962 16mm, Silent, Black & White, 110ft., 3min. Direct Viewing Camera Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 (reel no. 1) and TV scope records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 1961 Originally recorded in 16mm, Silent, Black & White, 150ft., 4min. Direct Viewing Camera Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March16, 1961 (Reel no. 1) and TV Scope Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 (Reel no. 2) 1961 16mm, Silent, Black & White, 290ft., 8min. Ditching - A-26 (Part 2) 16mm, Silent, Black & White Ditching A 20-A Catapult 16mm, Silent, Black & White Ditching tests were made at the outdoor ditching catapult on a 1/10-scale model of the army A-20A airplane with full-scale weight of 17, 400 lbs. and flaps semi-fixed in the down position. Power off; high, medium, and low attitude; landings were made in smooth water and along the waves with the bomb-bay doors, the bombardier's sighting window, and the rear gun hatch removed since it was assumed that they would fail in full-scale ditchings. The model, of wooden construction, was ditched at angles of attack of 13-degrees, 9-degrees, and 4-degrees; and at airspeeds of 88, 102, and 118 MPH. Ditching-- A-20, B-26, B-25, B-17 16mm Ditching A-26 (Part III) 16mm, Silent, Black & White Ditching and Hydro-Ski Landing Tests of a 1/10-Scale Model of the Chance Vought Regulus I Missile 1957 16mm, Silent, Black & White, 250ft., 7min. Ditching B-24 with Eagle Ant. 16mm, Silent, Black & White Ditching tests were made on a 1/16-scale model of the Army B-24 airplane equipped with an Eagle antenna. The nose window, nose-wheel doors, bomb-bay doors, belly turret, and rear entrance hatch were removed to simulate their failure. The model was ditched with and without the antenna installed and dived each time. Tests were run at attitude angles of 9-degrees (tail down) and 1-degree (near level) and speeds of 100 and 120 MPH (full-scale). Ditching B-24 with Parachutes 16mm, Silent, Black & White Ditching tests were made in Tank #2 on a 1/16-scale model of the Army B-24 airplane equipped with tow 1/16 scale 24-ft. parachutes, attached to the leading edge of the wing at the root chord and at each waist-gun window. The nose window, nose-wheel doors, belly turret and rear entrance hatch were removed to simulate their failure. The model was launched from 1, 6, and 10 in. above the water at launching attitudes of 9-degrees (tail down) and 1-degree (near level); and speeds of 100 and 120 MPH (full-Scale). The parachutes opened over and under the horizontal tail. Ditching Boeing B-47 16mm, Silent, Black & White Ditching- Calm Water B-24 and B-17 Calm water ditching tests of Y16-size models of the Army B-24 & B-17 in Tank No. 2 16mm Ditching Chance Vought F7U-3 Part-3 16mm Ditching- Convair Liner- Part 1 16mm, Silent, Black & White Ditching- D-36, Part II 1947 Ditching tests of a1/20-scale model of the Army B-36 airplane. 16mm, Silent, Black & White Ditching Grumman F9F-2 Airplane--Part 1 16mm, Silent, Black & White Ditching Investigation Douglas C-124 (Film for Report 1347) 16mm, Silent, Black & White Ditching Investigation of a 0.043-Scale Model of the Boeing Jet Transport--Part I 16mm, Silent, Black & White, 125ft., 3min. Ditching Investigation of a 1/20-Scale Model of Space Shuttle Orbiter 1975 16mm, 390ft., 10.5min. Ditching Investigation of a 1/25-Scale Model of the Douglas YC-133 Airplane Part 1 16mm, Silent, Black & White, 170ft., 7min. Ditching Investigation of a 1/30-Scale Dynamic Model of a Heavy Jet Transport Airplane 1971 16mm, Silent, Color Ditching Investigation of a Dynamic Model of a HU2K-1 Helicopter 1961 16mm, Silent, Color, 165ft., 5min. Ditching Investigation of a Jet Transport with Various Engine Installations 1956 16mm, Silent, Black & White, 230ft., 9.5min. Ditching Model North American B-45 16mm Ditching-- Northrop C-125 Airplane- Part 1 16mm, Silent, Black & White Ditching of 1/12-Scale Model of the F3D-2--Part I. 16mm Ditching Preformance in the Army B-26 Plane 16mm, Silent, Black & White Ditching tests were made using the seaway catapult at Langley Field, VA., on a 1/12-scale dynamic model of the B-26 airplane in an over-load weight condition and a Half-fuel, no bomb-load condition; with flaps fixed in the down position. High, medium, and low attitude landings were made in smooth water; across waves, into wind; across wind, along waves; at airspeeds ranging from 110 to 145 MPH, weights of 26,200 and 35,000 lbs., and at attitude angles ranging from 13-degrees to 4-degrees. Ditching Test of a 1/10-Scale Model of the North American XFJ-1 Model 243 16mm Ditching tests of a 1/10-scale model of the North American FJ-1 airplane were made in calm water at the Tank #2 monorail to determine the effect of landing attitude in landing flaps, and damage on the ditching behavior of the airplane. Scale strength flaps were used and all values, including weight of 12,151 lbs. and C.G. at 162.15 in. aft of station 0 and 11.12 in. below the fuselage reference line, were full scale. Tests were made with no damage simulates; with the nose-wheel door dented and crumpled. Skipping caused by the curvature of the underside of the fuselage, was noticeable at all conditions but was most violent in the undamaged condition. Attitude angles were 12-degrees, 8-degrees, and 2-degrees; flap deflections were 0-degrees and 40-degrees; and speeds were 93.9, 104.3, 118.2, and 128.7 knots. The landing flaps always failed and had no detrimental effect on the ditching behavior; therefore, most tests were made with the flaps extended at 40-degrees. The preferred attitude for ditching was found to be 12-degrees. Ditching Tests Douglass DC-4 and DC-6 Part 1 16mm, Silent, Black & White Ditching Tests Lockheed Constellation Airplane with Speedpak Attached- Part 2 16mm, Silent, Black & White Ditching tests were made in Tank #2 on a 1/18-scale model of the Constellation with Speedpak attached. Tests were made in calm water at various attitudes, ranging from 4-degrees to 12-degrees, and flaps up or down and speeds ranging from 90 to 147 mph. The model is in the undamaged condition and scale-strength connections are used to attach the damaged Speedpak. Tests are also made with a scale-strength Speedpak attached. Ditching Tests Lockheed Constellation 16mm, Silent, Black & White Ditching tests were made in Tank # 2 on a 1/18-scale model of the Lockheed Constellation in calm water at landing attitudes ranging from 4-degrees to 12-degrees, with flaps both up and down and at speeds ranging from 85 to 171 mph. Tests were made on an undamaged model and on a model with scale strength bottom and landing gear doors removed. Ditching Tests Navy SB2C-1 (Pt. 1) 16mm, Silent, Black & White Ditching tests were made in calm water in Tank #2 on a 1/8-scale model of the Navy SB2C-1 airplane (Army A-25) to obtain effect of attitude, damage, flap setting and the effect of the arresting gear hook upon ditching. Gross Weight of the airplane was 12,060 lbs.; C.G. at 30.2% MAC and 1.2 in. below the thrust line auxiliary elevators, near the top of the rudder, were used to obtain the desired attitudes; spoilers were placed on the wing at all speeds above 78.2 knots to decrease the lift to the proper value; and scale strength flaps were used. Test doors, removed; and with bomb-sight doors and bomb-lever doors, bomb-bay doors, removed; and with bomb-sight doors and bomb-lever doors removed; at attitudes of 80-degrees (intermediate) and 15-degrees (tail down); speeds of 86.6, 78.2, 104.3, 112.9, 60.8, 95.6, and 69.6 knots; maximum longitudinal decelerations of 1.2, 1.3, 4.0, 1.4, 1.8, 7.6, 5.2, 4.8, 2.3, 7.4, 5.1, and 4.2 g; lengths of run from 2 to 26 times the fuselage length; with flaps full up, half down, and full down. The effect of the arresting gear was to cause the behavior of the model to change from skipping and porpoising to a violent drive. Ditching Tests Navy XP2V-1-- Part 1 16mm Ditching tests of a 1/16 Scale model of the Navy XP2V-1 airplane were made in calm water at the Langley Tank #2 monorail to determine the effect of landing attitude, position of the landing flaps, damage, and ditching aid on the ditching behavior of the airplane. Scale strength flaps were used and all values, weight, 45,000lb., C.G. at 29.3% MAC and 3.1 in. above thrust line; are full scale. Tests were made with no damage simulated to determine the effect of re-enforcing the bottom of the fuselage sufficiently to withstand the water loads of a ditching to determine the hydrodynamic effect of the landing flap. The bottom of the fuselage is unusually weak and so would be difficult to reinforce adequately. Tests were made with the nose-wheel doors, main-wheel doors, bomb-bay doors, radar turret, rear entrance door, and tow sections of the fuselage bottom aft of the bomb bays removed to simulate their failure. In this condition, the model dived. The simplest method of eliminating this diving would be the installation of a hydroflap under the forward party of the fuselage. When the hydroflap was located at the forward edge of the nose-wheel, door, the model continued to dive; but when it was relocated at the aft part of the nose-wheel, door, the diving was prevented. Tests were made attitude angles of 10-degrees, 6-degrees, and 2-degrees; with flaps up and full down; over a speed range from 71 to 211 knots. Ditching Tests of Chance Vought XF6U-Model P1 16mm, Silent, Black & White Ditching tests of a 1/8-scale model of the Vought XF6U-1 Airplane were made in calm water at the Langley Tank #2 monorail to determine the effect of landing attitude, landing flaps, and damage on the ditching behavior of the airplane. Scale strength flaps were used and all values, including weight of 9,706 lbs. and C.G. at 32.0% MAC and 5.75 in. above the thrust line, are full scale. runs were made with no damage simulated, to determine the behavior of the undamaged model and the effect of the landing flaps; with the engine access panel, engine removable pane, arresting gear door, main landing gear doors, fuel-pump access door, catapult doors, gun-access doors, and nose-wheel door removed to simulator their failure; and with engine access panel, and the engine removable panel, and the engine mounding system at approximately scale strength, to more accurately determine the amount of damage to be expected on the after fuselage, and the resulting motions. With the model in undamaged condition, the landing flaps always failed and had no detrimental effect on the ditching behavior, however violent trimming up and skipping was due to the shape of the aft portion of the fuselage. The attitude angles were 12-degrees, 8-degrees, and 4-degrees; flap deflection was 27-degrees; and speeds were 97.3, 106.9, and 123.3 knots. Pictures of the typical bottom damage at all attitudes were shown when tests were made with scale strength portions mentioned above. Ditching Tests of the Navy XR6O-1 Airplane 1947 16mm, Silent, Black & White Ditching tests were made in calm water at the Tank #2 monorail on a 1/24-scale model of the Navy XR6[Organizational Source] National Advisory Committee for Aeronautics, Langley Aeronautical Lab., Langley Field, VA.-1 airplane to determine the effect of landing attitude, position of land flaps, and damage. Scale strength flaps were used. Model tests with no simulated damage were used to determine the performance that would occur if the bottom could be adequately reinforced to prevent damage during ditching. Tests were also made with simulated failure of the nose-wheel doors and simulated crumpling aft of the nose-wheel doors. The scale-strength bottom was made of a light balsa framework covered with waterproof tissue paper, built to break under a uniformly distributed load of 5 pounds per square inch (full scale). Attitude range from 1-degree to 9-degrees, the flaps were full up or full down, and the speeds ranged from 91-132 MPH. Ditching Tests-North American F-86 16mm, Silent, Black & White Tests were made in calm water at the Tank #2 Monorail on a 1/10-scale model of the North American F-86 to determine the effect of Landing Attitude, landing flaps, and damage of the ditching behavior of the airplane. Scale-strength flaps were used and the first tests were made with no damage simulated. All tests were run at attitudes of 14-degrees, 9-degrees, and 4-degrees; with flaps at 0-degrees or 38-degrees; and at speeds ranging from 98 to 132 knots. The behavior at 14-degrees and 9-degrees; is considered satisfactory but the dive at 4-degrees is undesirable. The underside of the aft fuselage is weak enough is to incur some structural failure in calm-water ditching, so the next runs were made with the simulated crumpled bottom installed. At this condition, the runs were shorter, and the decelerations were higher. Next the empty 207 gallon wing fuel tanks were attached and runs made. The tanks seemed to suck the model under, so it is preferred that the wing-fuel tanks be jettisoned before a ditch is attempted. The results show that the preferred ditching conditions are 14-degrees attitude, flaps deflected 38-degrees and a speed of 98 knots. Ditching XC-123 Part 1 Ditching investigation of a 1/14-scale model of the XC-123 Airplane. 16mm, Silent, Black & White Divergence and Flutter Tests of 0.4-Scaled Model of the ASROC Rocket Motor Fins 1958 16mm, Silent, Black & White D-M 1 Part 4 1946 16mm, Silent, Black & White Smoke flow investigation was made in the full-scale tunnel over the wing of the DM-1 glider with and without sharp leading edges. Flow with the airplane in the original configuration passed over the center section in conventional manner with tip vortices of small extent being seen occasionally at CL of 0.57 and an angle of attack of 15.8-degrees. With a semi-span sharp leading edges installed a large vortex originated at the apex of the triangle and extended backward over the wing at CL of 0.6 and an angle of attack of 16.6-degrees. Documentary Film Report on Wind Tunnel Test of 1/12-Scale Model of Lockheed Polaris Missile 1958 16mm, Silent, Color 8.5min. Documentary of Environmental Testing of Project ECHO and Vibration Survey of MERCURY-ATLAS 1 1961 16mm, Silent, Color, 980ft., 13min. Dr. Theodorsens Flutter in 8 ft. H.S.T 16mm, Silent, Black & White Drag Characteristics of Several Towed Decelerator Models at Mach 3 1970 Originally recorded in 16mm, Silent, Black & White, 70ft., 2min. Drop Tests of a 1/30 Dynamically Scaled Model of the AVCO WS-107A Booster Vehicle From a Simulated Bomb Bay of a B-52 Airplane 16mm, Silent, Black & White, 170ft., 7min. Dynamic Analysis for Shuttle Design Verification 1972 16mm, Silent, Black & White, 4min. Dynamic Investigation of a Landing-Gear Configuration consisting of a Single Main Skid and a Nose Wheel 1960 16mm, Silent, Black & White, 250ft., 7min. Dynamic Model and Drogue Parachute Tests for 1/10-Scale Model of the NASA Manned Satellite in the Langley 20-Foot Free-Spinning Tunnel 1959 16mm, Silent, Black & White, 195ft., 8min. Dynamic Model Investigation of a 1/20 Scale Gemini Spacecraft in the Langley Spin Tunnel 1963 16mm, Silent, Black & White, 360ft., 18min. Dynamic Model Investigation of a 1/s0 Scale Gemini Spacecraft in the Langley Spin Tunnel 1963 Originally recorded in 16mm, Silent, Black & White, 360ft., 18min. Dynamic Model Investigation of Some Landings and Slideouts of Recoverable Booster 1966 16mm, Silent, Color, 75ft., 2min. Dynamic Model Investigation of the Landing Characteristics of a Manned Spacecraft 1964 Originally recorded in 16mm, Silent, Color, 215ft., 6min. Dynamic Model Investigation of the Rough Water Landing Characteristics of a Space Craft 1966 Originally recorded in 16mm, Silent, Color, 135ft., 3.5min. Dynamic Model Investigation of Water Pressures and Accelerations Encountered During Landings of the Apollo Spacecraft 1967 Originally recorded in 6mm, Silent, Color, 205ft., 5.7min. Dynamic Model Tests at Low Subsonic Speeds of Project Mercury Capsule Configurations with and without Drogue Parachutes 1960 16mm, Silent, Black & White, 300ft., 8.5min Dynamic Model Tests of Models in the McDonnell Design of Project Mercury Capsule in the Langley 20-Foot Free-Spinning Tunnel 1959 Originally recorded in 16mm, Silent, Black & White, 1285ft., 36min. Dynamic Model Tests of Models of the McDonnell Design of Project Mercury Capsule in the Langley 20-Foot Free-Spinning Tunnel 1961 16mm, Silent, Black & White, 800ft., 22min. Dynamic Model Tests of Project Mercury Capsules in the Langley 20-Foot Free-Spinning Tunnel 1959 16mm, silent, Black & White, 550ft., 15.5min. Dynamic Stability and Control Characteristics of a Cascade-Wing Vertically-Rising Airplane Model in Take-Offs, Landings, and Hovering Flight 1954 16mm Film, Silent, Black & White, 365ft., 10min. Dynamic Stability and Control Characteristics of a Ducted Fan Model in Hovering Flight 1954 16mm Film, Silent, Black & White, 230ft., 6.5min. Dynamic Stability Tests of Full-Scale Minneapolis Honeywell Hemosphere-Drogue Combinations in the Langley 20-Foot Vertical Wind Tunnel 1960 16mm, Silent, Black & White, 230ft., 6min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1958 16mm, Silent, Black & White, 175ft., 5min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1958 16mm, Silent, Black & White, 310ft., 8.5min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1985 16mm, Silent, Black & White, 150ft., 4min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A. 1958 16mm, Silent, Black & White, 520ft., 14.5min. Dynamics of Anti-Skid Braking Systems 1982 16mm, Silent, Color, 600ft. Dynamics of Disk Galaxies 1969 16mm, Silent, Black & White, 205ft., 5.5min. Early Paraglider Tests 1962 16mm, Silent, Color, 12min Echo I 41-Foot Vacuum Sphere Ejection Tests 1965 16mm, Silent, Black & White, 485ft., 13.5min. Echo II 60-Foot Vacuum Chamber Sphere Ejection Tests 1965 16mm, Silent, Black & White, 323ft., 9min. Effect of Aerodynamic Heating on Flutter 1957 16mm, Silent, Black & White, 145ft., 4min. Effect of Chamber and L.E. on Unsteady Flows Past Thin Airfoils Mounted in 4""x19"" Tunnel. 16mm, Silent, Black & White Effect of Deflecting Ailerons with the Spin (Stick right in a Right Spin) on Recovery 16mm, Silent, Black & White, 190ft., 8min. Effect of Forward Protruding Nose Spikes on Blunt Shape Bodies at M=2.91 16mm, Silent, Black & White, 240ft., 6.5min. Effect of Gross Load Coefficient C [Delta Omega], on Bow Spray 16mm Effect of Gross Load Coefficient C^o, On Bow Spray 16mm Effect of Load-Alleviating Structure on the Landing Behavior of a Reentry-Capsule Model. 1961 Originally recorded in 16mm, Silent, Color, 77ft., 2min. Effects of the Atmospheric-Lithostatic Pressure Ration on Explosive Craters in Dry Soil 1971 16mm, Sound, Color, 25min. Effects of Wing Position and Vertical-Tail Configuration on Stability and Control Characteristics of a Jet-Powered Delta-Wing Vertically Rising Airplane Model. 1957 16mm, Silent, Black & White Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 165ft., 12min. Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 310ft., 8.5min. Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 215ft., 6min. Ejection and Inflation Test in 41-Foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 315ft., 9min. Ejection and Inflation Test in Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 160ft., 4.5min. Ejection and Inflation Tests in 41-Foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 175ft., 5min. Electra Model Investigation of Propeller Autoprecession 1961 16mm, Silent, Color, 320ft., 9min. Electric Arc Facilities 1962 16mm, Silent, Black & White, 240ft., 7min. Electron Beam Corner Flow Visualization 1967 16mm, Silent, Color, 77ft., 2.1min. Electron Beam Flow Visualization Studies on McDonnell-Douglas Aircraft Corp. Space Shuttle Concepts 1971 16mm, Silent, Color, 400ft. 11min. Elevated-Temperature Tests Under Static and Aerodynamic Conditions on Corrugated-Stiffened Panels 1959 16mm, Silent, Black & White, 450ft., 13min. Energy Efficient Flight (1974 Inspection Film) 1975 16mm, Sound, Color, 610ft., 17min. Erect and Inverted Parachute Recovery Tests of a 1/25-Scale Model of the Douglas F5D-1 Airplane 1956 16mm, Silent, Black & White, 320ft., 13min. Erect and Inverted Spin and Recovery Tests on the 1/40-Scale Model of the B-58 Airplane 1960 16mm, Silent, Black & White, 910ft., 25min. Erect Spin Tests of a 1/25-Scale Model of the Douglas F5D-1 Airplane 1955 16mm, Silent, Black & White, 760ft., 31min. Essex Carrier Smoke Flow 1945 16mm, silent, b/w Since a great deal of smoke was emitted from the guns on the Essex class aircraft carrier on firing, tests were run to determine which areas of the carrier were free from smoke so that fire stations could be set up in those areas, and therefore defense against enemy planes would be better since visibility would be clearer in those areas. The tests were made at airspeed of 1 MPH for all conditions and with deck guns pointing to bow, astern and broadside; with 5 in. turret guns parallel to the center line of the ship, to starboard, and to port; and angles of fire deck guns on port, high and low, and on starboard, high and low; at angles of yaw of the carrier of O, 30, 60, and 90 degrees to the right and left. Essex Carrier Smoke Flow 1945 16mm, Silent, Black & White Since a great deal of smoke was emitted from the guns on the Essex class aircraft carrier on firing, tests were run to determine which areas of the carrier were free from smoke so that fire stations could set up in those areas, and therefore defense against enemy plane could be better since visibility would be clearer in those areas. The tests were made at airspeed of 1MPH for all conditions and with deck guns pointing to bow, astern, and broadside; with 5 in. turret guns parallel to the center line of the ship, starboard, and to port; and angles of fire deck guns on port, high and low, and on starboard, high and low; at angles of yaw of the carrier of 0-degrees, 30-degrees, 60-degrees, and 90-degrees to the right and left. EVA Assembly of Large Space Structure Element 1981 Originally recorded in 16mm, Silent, Color, 25min. Evaluation of a Full-Scale Lunar Gravity Simulator comparsion of Landing-Impact Tests of a Full-Scale and a 1/6-Scale Model 1968 16mm, Silent, Color, 411ft., 11.5min. Evaluation of Gravity Simulation Technique for Studies of Man's Self of Locomotion in Lunar Environment 1963 16mm, Silent, Color, 315ft., 9min., Evolution of a Cylindrical Galaxy 16mm, Silent, Black & White Excerpt From Langley Research Center's XC-142 Terminal Area Flight Program-Nov 1968 to May 1970 1970 16mm, Silent, Color, 364ft.,10min. Excerpts from test Films Langley Impacting Structures Facility, Lunar Module 1968 Originally recorded in 16mm, Sound, Color, 105ft., 3min. Experimental Ablation Cooling 1958 Originally recorded in 16mm, 9 minutes, 330 feet, silent, b/w Experimental Ablation Cooling 1958 16mm, Silent, Black and White, 330ft., 9min. Experimental Design Studies and Flow Visualization of Proportional Laminar Flow Fluidic Amplifiers 1979 16mm, Sound, Color, 713ft., 26min. Experimental Ditching of a B-24 Airplane 16mm, Silent, Black & White, 924ft. Experimental Investigation of Aerodynamic Phenomena as Affected by Compressibility 16mm Experimental Investigation of Liquid Impact in a Model Propellant Tank 1965 16mm, Silent, color 185ft., 5min. Experimental Investigation of the Dynamic Stability and Controllability of a Towed M-2 Entry Vehicle Model 1964 16mm, Silent, Color, 375ft., 10min. Experimental Investigation of the Dynamic Stability of a Towed Parawing Glider Air Cargo Delivery System 1964 16mm, Silent, Color, 688ft., 19min. Experimental Investigation of the Dynamic Stability of Towed Parawing Glider Model 1962 16mm, Silent, Color 165ft., 4.5min. Experimental Investigation of the Landing Dynamics of Three Legged Spacecraft Models. 1974 16mm, Silent, Color, 4.5min. Experimental Research in Aerospace and Structural Dynamics 1964 16mm, Sound, Black & White, 590ft., 16.5min Experimental Studies of Rotational Fluid Sloshing 1961 16mm, Silent, Color, 490ft., 13min. Exploratory Investigation of Factors Affecting the Wing Tip Vortex 1972 16mm, Silent, Color, 638ft., 17.75min. Exploratory Study of Man's Self-Locomotion Capabilities with a Space Suit in Lunar Gravity 1964 16mm, Sound, Color, 360ft., 10min. Exploratory Study of Ventilated Flows About Yawed Surface -Piercing Struts 1959 16mm, Silent, Black & White, 200ft., 5min. Reported herein are the results of observations and measurements made in connection with a study of the phenomenon of the development of atmosphere-connected cavities about surface-piercing struts. Conditions for the existence of such ventilated flows which have been derived from the experimental data are presented. In addition, certain broad conclusions pertinent to model testing and full-scale design are reached. Further experimentation to define the inception of ventilation as a function of boundary-layer state or Reynolds number is required. Exploratory Tests of Several Cooling Schemes at High Stagnation Temperature 1957 16mm, Silent, Color, 200ft., 5.5min. Exploratory Wind Tunnel Investigation of Deployable Flexible Ventral Fins for Use as Emergency Spin Recovery Device 1971 16mm, silent, Color, 130ft., 3.5min. Explorer XII (S-3) Energetic Particles Satellite 1962 16mm, Sound, Color, 600ft., 17min. External Mixing Spray Gun Nozzle, Langley Innovations Film 1963 16mm, Sound, Color, 165ft., 4.5min. External Wing Fuel Tanks Used as Ditching Aids 1956 16mm, Silent, Black & White, 240ft., 10min. F.F.T. 16mm F.S.T Smoke Over Wing 16mm, 296ft. F.S.T. P-46 Tufts 16mm F.S.T. Smoke Over Transport Film No. F-105 Vapor Screen Test 16mm, Silent, Black & White, 60ft, 1.5min F2H-4 Radar Tracking Performed by VMF-L14 at MCAS, Cherry Point, N.C. for NACA, Langley Field, Va. 16mm, Silent, Black & White F-40-2677 1960 16mm, Silent, Color, Black & White, 413ft., 11.5min. F-40K Flight (Extra) Tuft studies of flow over horizontal and vertical tail surfaces of the Curtiss P-40K in flight are shown. 16mm F6F-Flutter Model 16mm F-8U Main Landing Gear Tests 1962 16mm, Silent, Color, 120ft., 3.5min. Fairchild C-82 Tests 1950 16mm, Silent, Black & White Tests were made in calm water in Tank #2 of a 1/15-scale model of the Fairchild C-82 airplane with landing flaps full down; with no damage simulated; with failure of nose-wheel doors, and aft cargo doors simulated; and with failure of nose-wheel, aft cargo doors, and paratainer hatch simulated; at attitude angles of 2-degrees, 7-degrees, and 12-degrees; over a full-scale speed range from 90 to 125 MPH. Of the three conditions of damage tested the last condition is most likely to occur in Full-scale ditchings. if this damage occurs, the cargo compartment will be a hazardous ditching station because of the rapid inrush of water. Fast Flight 1979 16mm, Silent, Color Fatigue Failures of Simple Panels Due to Intense Noise 16mm, Silent, Black & White, 100ft., 4min. Fatigue Film Cleveland Conference 1950 16mm, Silent, Black & White Fault Tolerant Multi Processor for Commercial Aircraft 16mm, 490ft., 13.5min. FFT Film to Accompany Paper ""Technique for Testing Models of VTOL and STOL Airplanes"" 1956 AGARD Meeting at Brussels, Belgium August 27 - 31, 1956 16mm, 20.5min FFT Hinged Tip Sequence Tech Film #18 16mm, Silent, Black & White Flight tests were made in the free-flight tunnel to determine the effect on lateral stability and control of fuel-carrying wing-tip extensions hinged so at to reduce the loads imposed on with structure. The wing-tip extensions of the model were ballasted to represent tips loaded with fuel and having about the same wing loading as the model without the tip extensions. With the tips fastened rigidly, the model flies more smoothly than the basic model because of the increased damping in roll and the higher moments of inertia. The higher moments of inertia, however, make it more difficult to control. with the tips hinged to the chordwise axis the model is more difficult to fly than when the tip are rigidly attached because of the erratic motions of the tips. The tip hinge axis skewed 20-degrees, the tip movement is reduced, but still large and the model does not fly well. The skew angle was increased to 45-degrees and although the amplitude of the tip motions were reduced, they were still objectionably large. Next tests were made with wing tips with 14% chord flaps linked to move up when the tip went up and down and the tip went down. The flaps were geared to give 20-degrees deflection for 1-degree tip deflections. These linked flaps, although theoretically only as effective as the 45-degree skewed hinge line, resulted in smaller tip motions and mad the model easier to fly. With a 20% chord flap and gearing increased to 3-degrees flap for 1-degree tip movement of the tips relative to the wing was virtually eliminated, and the model was easier to fly. FFT-Stability Control-- Tests Straight Wing Vertically Rising Airplane Take-Off, Landing, Hovering 16mm, Silent, Color Film of Free-Flight Tunnel Radio Control Activities 1956 16mm, Silent, Color, 430ft., 17min. Film on Computer Seminar 1968 16mm, Silent, Black & White Film Supplement to Low-Speed, Free-Flight Stability Test of a 1/10-Scale Model of the AVCO Reentry Shape 52 1957 16mm, Silent, Black & White, 44ft., 1.25min. Film Supplement to Paper Entitled ""Some Stability Problems of Vertically Rising Aircraft. 1955 16mm, Silent, Black & White, 422ft., 17min. Film Tests of Lockheed F-104 Model 16mm, Silent, Black & White, 100ft., 4min. Film to Accompany Paper Entitled Research on VTOL and STOL airplanes in the United States. Presented in Madrid Spain 1958 16mm, Silent, Color, 22.5min. Film to Accompany Talk Given by Charles H. Zimmerman to British Helicopter Society 1958 16mm, Silent, 280ft. Film Used at Meeting of High-Speed Aerodynamics Subcommittee. Wallops Island, Va, August 31, 1954. 1954 16mm, Silent, Color, 340ft., 14min. Film Used by Paul Hill in NACA Conference; November 1,2,3, 1955 1955 16mm, Silent, Color, 170ft., 7min. Fin Heating at High Stagnation Temperatures 16mm, Silent, Color, 560ft., 16min. Fire!! 16' Wind Tunnel 1950 This color film was made on Monday afternoon, Feb. 20, 1950 during the fire in which the tower on the 16-foot high-speed tunnel at Langley Laboratory burned. Firing Tests of Spherical Rocket Motors 1958 16mm, Silent, Color 750ft., 21min. First and Second Developmental Flight Test of Echo II (A-12) Spacecraft 1965 16mm, Silent, Black & White, 192ft., 5.5min. First Developmental Flight Test of A-2 Spacecraft 1962 Originally recorded in 16mm, Silent, Black & White First Flight of the F8-SCW 16mm, Silent, Color Five-Stage Hypersonic Flight Test in GE-PARD Ablation Investigation. Model no. H50-2842 1958 16mm, Silent, Color Five-Stage Hypersonic Free-Flight Research Vehicle 1958 16mm, Silent, Color 525ft., 14.5min. Flexible Wing Concept 1960 16mm, Silent, Color, 750ft., 21min. Flexible Wing Concept Made in 1961 1962 16mm, Silent, Color, 480ft., 15min. Flexible Wing Research and Development 1962 16mm, 380ft., 11min. Flight Demonstration of the Time Reference Scanning Beam Microwave Landing Systems 16mm, Sound, Color, 800ft., 22min. Flight Investigation of a V/STOL Transport Model Having Six Wing-Mounted Lift Fans 1971 16mm, Silent, Color, 220ft., 6min. Flight Investigation of a V/STOL transport Model With Four Pod-Mounted Lift Fans 1971 16mm, Silent, Color, 182ft., 5min. Flight Investigation of Dynamic Stability and Control Characteristics of a 1/10-Scale Model of a Variable Wing-Sweep Fighter Airplane Configuration 1967 16mm, Silent, Color, 305ft., 8.5min. Flight Investigation of Stability and Characteristics of a 1/4-Scale Model of a Tilt-Wing Vertical Take-off and Landing Aircraft 1957 16mm, Silient, Black & White, 665ft., 18min. An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a tilt-wing vertical-take-off-and-landing aircraft with the use of a remotely controlled 1/4-scale free-flight model. The model had two propellers with hinged (flapping) blades mounted on the wing which could be tilted up to an incidence angle of nearly 90 deg for vertical take-off and landing. The investigation consisted of hovering flights in still air, vertical take-offs and landings, and slow constant-altitude transitions from hovering to forward flight. The stability and control characteristics of the model were generally satisfactory except for the following characteristics. In hovering flight, the model had an unstable pitching oscillation of relatively long period which the pilots were able to control without artificial stabilization but which could not be considered entirely satisfactory. At very low speeds and angles of wing incidence on the order of 70 deg, the model experienced large nose-up pitching moments which severely limited the allowable center-of-gravity range. Flight Investigation of Stability and Control characteristics of a 0.18-Scale Model of a Four Duct Tandem V/STOL Transport 1965 16mm, Silent, Color, 300ft., 8.5min. Flight Investigation of Stability and Control Characteristics of a 1/8-Scale Model of a Tilt-Wing Vertical Take-off and Landing Aircraft 1958 16mm, silent, Color, 1220ft., 34min. Flight Investigation of Stability and Control Characteristics of a 1/9-Scale Model of a Four Propeller Tilt-Wing V/Stol Transport 1964 16mm, Silent, Color, 625ft., 17min. Flight Investigation of the Dynamic Stability and Control Characteristics of a 0.18-Scale Model of a Fan-In-Wing VTOL Airplane. 1966 16mm, Silent, Color, 255ft., 7min. Flight Research with the Wing Flow Method 16mm, Silent, Color Flight Service Evaluation of PRD-49 Epoxy Panels on L-1011 Commercial Aircraft 1973 16mm, Sound, Color, 6.5min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1957 16mm, Silent, Color, 385ft., 11min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1957 16mm, Silent, Color, 115ft., 3min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1958 16mm, Silent, Color, 62ft., 2min. Flight Test of 0.12-Scale Rocket-Boosted Model of NAVAHO II Model No.2 16mm, Silent, Black & White, 75ft, 3min Flight Test of 0.12-Scale Rocket-Boosted Model of NAVAHO II Model No.2 16mm, Silent, Color, 50ft, 2min Flight Test of 1/4-Scale Model No. 2 of Hermes A-3B Missile, Wallops Island, Va 1954 16mm, Silent, Black & White Flight Test of 31.2 Diameter Modified Ringsail Parachute Deployed at Mach 1.39, Dynamic Pressure 11 Pounds Per Square Foot 1967 Originally recorded in 16mm, Silent, Color, 120ft., 3.5min. Flight Test of a 0.12-Scale NAVAHO II Rocket Model 16mm, Silent, Color Flight Test of a 1/10-Scale Rocket-Powered Model of the Douglas XF4D-1 Airplane 16mm, Silent, Color, 95ft, 3.5min Flight Test of a 30-Foot Nominal Diameter Cross Parachute Deployed at Mach 1.57 and Dynamic Pressure of 9.7lbs/square ft 1968 Originally recorded in 16mm, Silent, Color, 120ft., 3.5min Flight Test of a 30-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at Mach 1.56 and Dynamic Pressure of 11.4 Pounds Per Square Foot. 1967 Originally recorded in 16mm, Silent, Color 100ft., 3min. Flight Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 2.72 and a Dynamic Pressure of 9.7 Pounds Per Square Foot. 1968 Originally recorded in 16mm, Silent, Color, 111ft., 3min. Flight Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 3.31 and a Dynamic Pressure of 10.6 Pounds Per Square Foot. 1969 Originally recorded in 16mm, Silent, Color, 116ft., 3.2min. Flight Test of a 40-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 1.91 and a Dynamic Pressure of 11.6 Pounds per Square Foot 1968 Originally recorded in 16mm, Silent, Color, 180ft., 5min. Flight Test of a Delta-Wing Jet-Powered Vertically Rising Airplane Model 1965 16mm, Silent, Color, 480ft., 13min. Flight Test of a0.13 Model of the Dornier D0-31 VTOL Airplane 1963 16mm, Silent, Color, 470ft., 13min. Flight Test of Bull Pup Missile at Wallops Island, Va. 1956 16mm, Silent, Color, 286ft., 8min. Flight Test of Chance Vought XF8U-1 Rocket Model No. 5 16mm, Silent, Color, 60ft, 2.5min Flight Test of Model D117-2484 1958 16mm, Silent, Color, 13min. Flight Test of Nike-Cajun Sounding Rocket 1956 16mm, Silent, Color, 125ft., 3.5min. Flight Test of the 7.5 Percent Scale Rocket-Boosted Model of the Martin WS-302A at Wallops Island, Va. 35mm, Silent, Black & White Flight Tests and Tuft Tests of 1/8-Scale Model of Bell D188A Jet VTOL Airplane in the Conventional Flight Condition 1958 16mm, Silent, Black & White Flight Tests in the Langley Full-Scale Tunnel of a 1-7 Scale-Model of the North American X-15 Airplane. 1958 16mm, Silent, Black & White, 605ft. 17min. Flight Tests in the Langley Full-Scale Tunnel of a Model with Horizontal Tail Used for Roll Control 1957 16mm, Silent, Black & White, 357ft., 10min. Flight Tests of ""TART"" Missile at the Pilotless Aircraft Research Station, Wallops, Va 1958 16mm, Silent, Color Flight Tests of 0.13-Scale Model Convair XFY-1 Vertical Rising Airplane Lower Vertical Tail Removed 16mm, Silent, Color Flight Tests of a 0.13-Scale Model of the Convair XFY-1 in Set-Up Simulating Proposal for Captive Flight Tests in a Hanger (Supplement to RM-SL54B16a). 16mm, Silent, Black & White Flight Tests of a 0.4-Scale Model of Stand-On Type Vertically Rising Aircraft 1954 16mm, Silent, Black & White, 320ft., 9min. Flight Tests of a 1/6-Scale Model of the Hawker P 1127 Jet VTOL Airplane 1961 16mm, Silent, Black & White, 14min. Flight Tests of a 1/8-Scale Model of the Bell D-188A Jet VTOL Airplane. TED No. AD 3147 1958 16mm, Silent, Black & White Flight Tests of a 40-Foot Nominal Diameter Modified Ringsail Parachute Deployed at Mach 1.64 and Dynamic Pressure of 91 Pounds Per Square Foot 1967 Originally recorded in 16mm, Silent, Color, 120ft., 3.3min. Flight Tests of a Model of a High Wing Transport VTO Airplane with Tilting Wing and Propellers and with Jet Controls at the Rear of the Fuselage for Pitch and Yaw Control 16mm, Silent, Color, An investigation of the stability and control of a high-wing transport vertical-take-off airplane with four engines during constant-altitude transitions from hovering to normal forward flight was conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with the thrust axes in the wing chord plane. The wing could be rotated to 90 degrees incidence so that the propeller thrust axes were vertical for hovering flight. An air jet at the rear of the fuselage provided pitch and yaw control for hovering and low-speed flight. Flight Tests of a Model Similar to the F8U-1 Airplane in the Langley Full-Scale Tunnel 1956 16mm, Silent, Black & White, 250ft., 10min. Flight Tests of a Model Similar to the F8U-1 Airplane in the Langley Full-Scale Tunnel 16mm, Silent, Color, 75ft., 3min. Flight Tests of a Vertically Rising Airplane Research Model Interchangeable Swept and Unswept 16mm, Silent, Black & White Flight Tests of Ducted Rocket with Conical Shock Nose Inlet 1958 16mm, Silent, Color Flight Tests of the 1/5 - Scale Boeing Dyna-Soar Model (2002) in the Langley Full-Scale Tunnel 1960 16mm, Silent, Black & White, 1620ft., 45min. Flight Tests of the NACA Ram-Jet Test Vehicle Using Continental Aviation and Eng. Co. Solid Fuel 16mm, Silent, Color, 68ft, 2.34min Flight Tests of Three Arcon Rockets Fired from Wallops Island, Va. 1958 16mm, Silent, Color, 31min. Flight Tests Results from Supersonic Deployment of an 18-Foot Diameter (5.49 meter) Towed Ballute Decelerator 1969 Originally recorded in 16mm, Silent, Color, 112ft., 3min. Flights Clippings 16mm Flights of Ryan N14ON by Ryan Pilot at NASA Langley Research Center 1962 16mm, Silent, Color, 250ft., 7min. Flights of Two-Foot Gilding Parachute Made January 7, 1965 1965 16mm, Silent, Black & White, 150ft., 4min. Flow Behind Cylinder as Shown by Tuft Grid 16mm, Silent, Black & White, 100ft., 2.75min. Flow on the Surface OF the Wing by the Ink-Flow Visualization Method (Swept Wing and Straight Wing) 1957 16mm, Silent, Black & White, 175ft., 5min. Flow Over Blunt Body at M=20 in 2-Inch Helium Tunnel 1960 Originally recorded in 16mm, Silent, Black & White, 27ft., 1min. Flow Past Two Dimensional Air Foils in the Langley 4X19 inch Simi-open Tunnel as obtained by a Schlieren System (3 Reels) 16mm, Silent, Black & White, 2680ft., 72min. Flow Studies of Decelerators at Supersonic Speeds 1959 Originally recorded in 16mm, Silent, Black & White, 350ft., 10min. Flow Studies on a 49-Degree Swept-Wing Model with Trailing-Edge and Leading-Edge Blowing Applied. 16mm, Silent, Black & White, 80ft., 2min. Flow Visualization in Cascades and Rotors- E. Boxer, ASME Meeting of November 1960 1960 16mm, Silent, Color and Black & White, 215ft., 6min. Fluctuations in Supersonic Inlets 16mm, Silent, Black & White The phenomenon of flow fluctuation in supersonic inlets is investigated at the following subcritical conditions. Tests were made at Mach number 1.92 on an inlet having 30-degrees cone and 12 to 17-degrees cowling and no internal contraction. The Mach number at the cone surface is 1.20. The subcritical condition is stable until the boundary flow is supersonic at the jet boundary. The system of throttling is then changed and fluctuation phenomena is completely modified. Frequency and amplitude of fluctuation changed when tests were made at Mach number 1.92 on an inlet having 20-degrees cone and 13-17-degrees cowling and on internal contraction. The Mach number at the cone surface of 1.51 is too high. The subcritical condition is not stable and no regulation of volume flow is possible. The remaining tests were made at Mach number 2.70. No stable subcritical condition was possible for an inlet having 22-degrees cone and 4 to 7-degree cowl and internal contraction, when the Mach number at the cone surface was 2.02, an inlet having 40-degree cone and 16 to 24 degree cowl and Mach number at the surface 1.23 was tested. In the final test an inlet having gradual external compression and a low mach number at the surface at the entrance was tested, but subcritical conditions were not stable because of the existence of separation. Fluid Motion in a Simplified Tip Tank Model 16mm, Silent, Color Fluid Motion in a Simplified Tip Tank Model 16mm, Silent, Color Flutter at a Glance 1981 16mm, Sound, Color, 2.5min. Flutter 16mm, Silent, Black & White Presents short discussion of flutter and illustrations of the separate modes of vibration possible for a wing to execute. Tests were made in the NACA High-Speed Tunnel on both plastic and dural wing models at speeds up to 500 MPH. Of increasing importance is flutter involving all three vibrations; bending, torsion, and aileron motion about the hinge. Any two or all of these motions must be present simultaneously for flutter exist. Illustrations of each of these motions and combinations are presented. Flutter Film Which Accompanies the Presentation of the 1957 Minta Martin Lecture By Prof. T. E. Garrick 1958 16mm, Silent, Black & White Flutter Investigation in the Langley Transonic Blowdown Tunnel of Models of the F8U-3 Airplane Wing 1957 16mm, Silent, Black & White, 850ft., 23.5min Flutter Investigation of 1/15-Scale Models of A2F-1 Horizontal Tail Conducted in Langley Transonic Blowdown Tunnel 1959 16mm, Silent, Black & White, 290ft., 8min. Flutter Investigation of Canard Model of Beech XKD2B-1 Expendable Powered Target Conducted in Langley Transonic Blowdown Tunnel 1960 16mm, Silent, Black & White, 250ft., 7min. Flutter investigation of Parawing Models in the Langley Transonic Dynamics Tunnel 1961 Originally recorded in 16mm, Silent, Black & White, 405ft., 11.5min. Flutter Investigation of Simplified Models of Dyna-Soar 1 Booster Fins in the Langley Transonic Blowdown Tunnel 1961 16mm, Silent, Black & White, 7min. Flutter of a Large Variety of Models in the Langley Transonic Blowdown Tunnel 1962 16mm, Silent, Black & White, 250ft., 7min. Flutter of A Large Variety of models in the Langley Transonic Blowdown Tunnel Originally recorded in 16mm, Silent, Black & White Flutter of Buckled Curved and Flat panel at M=1.3 and 2.0 1965 16mm, Silent, Black & White, 86ft., 2.5min. Flutter TBF-1 16' W.T. 16mm, Silent, Black & White Flutter tests were made on a full-scale TBF-1 aileron installation in the 16 ft. high-speed tunnel. The model tested was an outer section of a production wing panel of the TBF-1 airplane. Aerodynamic tests were made of the wing-aileron installation to determine whether the aileron had contributed to the failures that have occurred in the service of the airplane. Flutter of this tests model occurred at airspeeds of about 150MPH. On the TBF-1 the wing panel is attached at 2 points at approximately 10 and 40% chord, therefore, the chordwise stiffness is low. Lacking chordwise rigidity, chordwise motion occurred. The C.G. of the aileron is forward of the hinge line, and therefore classical wing-aileron flutter was not possible. However, the method of attachment of the aileron to the wing panel places the C.G. 2.17 in. above the hinge line. The aileron is, therefore, deflected by inertia forces when chordwise motion and its attendant chordwise accelerations occur. Rearward motion of the wing therefore produces of negative aileron angle and forward motion of the wing a positive aileron angle. The alternation up and down aileron produces simple wing bending due to lift changes. No torsional deflection of the wing evident. In order to verify the fact that the chordwise motion was essential to flutter condition, the chordwise rigidity was greatly increased by the insertion of a steel block between the tunnel wall and wing at approximately 80% chord. Flutter did not occur of this test condition and maximum tests speed was 365 MPH. The results of this analysis indicate that flutter involving chordwise motion of the wing can be prevented by 2 methods: (1) By stiffening the wing attachment in the chordwise plane. (2) By mass-balancing the aileron in the normal-to-chord plane. Flutter Test of Fin-Rudder Model in Langley Transonic Blowdown Tunnel 1957 16mm, Silent, Black & White, 115ft., 3min. Flutter Test of Full Scale X-15 Vertical Tail in Langley 9X6 Foot Thermal Structures Tunnel 1958 16mm, Silent, Black & White, 250ft., 7min. Flutter Test of Horizontal-Tail Models of F8U-3 Airplane Test 334 1957 16mm, Silent, Black & White, 560ft., 15.5min. Flutter Tests in the Supersonic Flutter Apparatus, March 7 and 13, 1956 1956 16mm, Silent, Black & White, 300ft, 12min. Flutter Tests of a Model of the F-105B Airplane Horizontal Tail with Circular Yoke in the Langley 26-Inch Transonic Blowdown Tunnel Test 331 1957 16mm, Silent, Black & White, 2680ft., 74min. Flutter Tests of All Movable Horizontal Tails in the Langley Transonic Blow-Down Tunnel 16mm, Silent, Black & White, 290ft, 8min Flutter Tests of Beech XKD2B-1 Target Drone in the Langley 8-Ft. Transonic Pressure Tunnel 1960 16mm, Silent, Black & White, 836ft., 23min. Flutter Tests of Bell Outer-Wall Insulating Panel. NACA Supersonic Blowdown Jet, Gas Dynamics Laboratory 1957 16mm, Silent, Color, 190ft., 5min. Flutter Tests of Centaur Transition Panel in Unitary Plan Wind Tunnel 1961 16mm, Silent, Black & White, 240ft., 6.5min. Flutter Tests of Hysail Model in 2-Foot Transonic Aeroplasticity Tunnel 1959 16mm, Silent, Black & White, 250ft., 7min. Flutter Tests of Hysail Models in 4- by 4-Foot Supersonic Pressure Tunnel 1959 16mm, Silent, Black & White, 1285ft., 36min. Flutter Tests of Model of Navy P6M-1 Tail in Langley 26-Inch Transonic Blowdown Tunnel 16mm, Silent, Black & White, 50ft., 2min. Flutter Tests of Model of Navy P6M-1 Tail in Langley 26-Inch Transonic Blowdown Tunnel. Test 229 16mm, Silent, Black & White, 145ft., 8min. Flutter Tests of Models of the Horizontal Tail and Wing of the F8U-3 in the Langley 9- by 18- Inch Supersonic Flutter Tunnel 1957 16mm, Silent, Black & White, 1760ft., 48min. Flutter Tests of the 1/8-Scale Full Span Lockheed Electra in the Langley Transonic Dynamics Tunnel 1960 16mm, Silent, Black & White, 1210ft., 33.5min. Flutter Tests of X-15 Tail Surfaces in the Langley 9- by 18-Inch Supersonic Flutter Tunnel 1958 16mm, Silent, Black & White Flutter Tests of X-15 Tail Surfaces in the Langley 9-by 18-Inch Supersonic Flutter Tunnel 1957 16mm, Silent, Black & White, 242ft., 7min. Flutter Tests of XPB2M-1 16mm Flutter tests were made on a model of the Martin PBM-1 seaplane to determine if a low flutter speed exists because of the elastic coupling between wing and engine, the ultimate flutter speed, and the wing divergence speed. Certain structural weaknesses were disclosed by the tests. The model, made of the plastic pyrolin has characteristic speed ratio of 3.61. Flutter speed calculation gave a value of 98.5 MPH corresponding to 355.6 MPH for the original seaplane. The calculated divergence speed was 95 MPH and the divergence first appeared at 94 MPH. Tin this case, divergence speed is less than flutter speed so no flutter appeared. It was concluded that the torsion axis is too far rearward, particularly at the tip; and no low flutter velocity is introduced by engine, which was proved to have a desirable effect on wing stability. In test # 1 the fuselage was freely suspended, angel of attack was 0-degrees, and airspeed ranged from 25 to 64 MPH. In test # 2 the left wing & fuselage were fixed, wing tip was overloaded, angles of attack were 0-degrees and 4-degrees, & airspeed ranged from 56.4 to 69 MPH. In test # 3, for angles of attack 2-degrees and 1.5-degrees and airspeed range 61.3 to 73.5 MPH, the fuselage & lead weight was attached to the leading edge to bring center of gravity forward. In test # 4 the fuselage was again freely suspended and both wings were free with lead weight on the leading edges, angel of attack was 0-degrees and airspeeds ranged from 74-96 MPH. Flutter Tests--Langley Transonic Blowdown Tunnel Grumman F11F-1 Models with Body Freedoms in Pitch, Roll and Vertical Deflection 1957 16mm, Silent, Black & White, 170ft., 5min. Flying Platform Research--Parts I and II. 16mm, Silent, Black & White, 175ft., 7min. Fourth Dimension 16mm, Sound, Color, 824ft. Free Drop Tests of Nondynamically Scaled Models of Minneapolis-Honeywell Fluted Spheres in the Langley 20-Ft. Free-Spinning Tunnel 1959 16mm, Silent, Black & White, 900ft., 25min. Free Flight Afterbody Heat-Transfer Investigation Supporting the WS-107A Project by the Pilotless Aircraft Research Division of the NACA Langley Laboratory 1958 16mm, Silent, Color Free Flight Afterbody Pressure Investigation Supporting the WS-107A Project by the Pilotless Aircraft Research Division of the NACA Langley Laboratory 1957 Originally recorded in 16mm, Silent, Color, 950ft., 26min. Free Flight Investigation of 0.15-Scale Model of Yf-16 Airplane at High Angles of Attack--Coord # AF-Am-135 1975 16mm, Silent, Color, 3.5min. Free Flight Investigation of 0.15-Scale Model of YF-17 Airplane at High Angles of Attack--Coord # AF-AM-135 1975 16mm, Silent, Color, 7min. Free Flight Investigation of 1/17-Scale Model of the B-1 Airplane at High Angles of Attack--Coord # AF-AM-128 1973 16mm, Silent, Color, 5.75min. Free Flight Investigation of Effect of Slats on Later Directional Stability of a 0.13-Scale Model of the F-4E Airplane 1971 16mm, Silent, Color, 200ft., 5.5min. Free Flight Investigation of Lateral-Directional Characteristics of a 0.10-Scale Model of the F-15 Airplane at High Angles of Attack--Coord # AF-AM-010 1973 16mm, Silent, Color, 4.5min. Free Flight Investigation of Radio Controlled Models with Parawings 1961 16mm, Silent, Black & White, 625ft., 17min. Free Flight Investigation of the Deployment of a Parawing Recovery Device for a Radio-Controlled 1/5-Scale Dynamic Model Spacecraft 1963 16mm, Silent, Color, 200ft., 5.5min. Free Flight Model Investigation of a Vertical Attitude VTOL Fighter 1975 16mm, Silent, Color Free Flight Model Investigation of Vertical Altitude VTOL Fighter with Twin Vertical Tails 1975 16mm, Sound, Color, 21min. Free Flight PRD Sphere and Conical Models Taken at 4000 FPS 1949 16mm This film was made for the purpose of determining if it was possible to use flash bulbs as a source of light for making movies of tests run in the tunnel. Pictures were made at 4000 frames per second of the bismuth and balsa, spherical and conical models shot from the compressed air gun in the tunnel. This method was found to be successful. Free Flight Tunnel Kaiser Hughes Tailless Airplane 16mm Flight tests were made in the free-flight and free-spinning tunnels on a model of the Kaiser-Hughes tailless airplane. In the free-flight tunnel the model was tested with original wing tip vertical tails, which gave large yaw angles when ailerons were used to hold wings level, and with wing tip tails replaced by equal area high aspect ratio tails at the trailing edge, which considerably reduced yawing. Unstable oscillations developed when elevators were not used. For the tumbling tests in the free-spinning tunnel, models of the Kaiser, Bell P-39 and Northrop N-9M airplanes were released in a nose-up attitude, simulating a whip stall. The air-speeds were 19 and 39 fps. The P-39 went into a dive and would not tumble, and the N-9M tumbled sometimes and went into a dive sometimes. Free Flight Tunnel N-1M 1940 16mm Stability and control tests were made in the free-flight tunnel on the Northrop N-1M tailless plane. Tests were made with vertical tail added on boom to correct initial poor lateral behavior, with horizontal tail added to boom to correct pitching motion, with vertical tail removed, with both tails and boom removed and with rudders rigged up 150-degrees. Lateral oscillations due to reduced directional stability resulted when rudders were rigged up 150-degrees. C.G. positions were 19%, 26%, 21% and 17% of MAC. Free Flight Tunnel N-1M 1941 16mm Final stability and control tests were made on the Northrop N-1M tailless airplane model in the free-flight tunnel. The wing tips were turned down 45-degrees to improve lateral stability and control. Ailerons alone were used for control and adverse yawing due to the ailerons caused difficulty in controlling the model. Weights were added fore and aft on center line to improve longitudinal behavior, but stability and control were unaffected. Weights were add at wing tips; this caused difficulty in flying the model. Lateral control appeared weaker and damping of lateral oscillations was light. C.G. positions were 16% and 17% MAC. Free Flight Tunnel Tailless Model Consolidated Vultee-- Part II 1944 16mm Reel 1 presents flight tests made in the free-flight and free spinning-tunnels on a 1/30 scale model of the Consolidated-Vultee Tailless airplane. Tests were made with and without slots, with vertical tail surfaces on the fuselage, with tip vertical tail surfaces, or no tail surfaces; with no propellers or propellers windmilling. In the flaps down condition, extensible horizontal tail surfaces appear, but they form fort of the trailing edge of the wing in the flaps up condition. Reel 2 presents flight tests made in the free-flight tunnel on a 1/35 scale model of revised consolidated-Vultee tailless airplane in the flaps up condition. The model has tufts on the root of the wings showing air flow over the wing. Free Flight Tunnel Tailless Model Consolidated-Vultee- Part II 1944 16mm Flight tests were made in the free-flight tunnel on a 1/30 scale model of Consolidated-Vultee Tailless airplane with flaps up and down. A comparison is made by showing flights of a conventional twin-engine bomber design. Free Flight Tunnel Tests Cascade Model Hovering Flight 16mm, Silent, Black & White, 345ft., 10.5min. Free Flight Tunnel Tests of a 1/10-Scale Model of the Convair F-102A (MX-1554) Airplane 16mm, Silent, Black & White Free Flight Tunnel Tests, Consol. Vultee XP 92 1947 Power-off Stability and control tests of the 1/12 scale model of the Consolidated CV-7002 airplane (flying mock-up of XP-92) were conducted in the free-flight tunnel at the request of the air Materiel Command, Army Air Forces. All Flights were made with a C.G. location of the 0.25 MAC. For the heavy wing loading of approximately 2.27 lbs./sq.ft., the weight and moments of inertia were scaled down from the full-scale airplane. A light with loading of approximately 1.79 lbs./ sq. ft. was also used. The control used on the model is a 'Flicker' (full-on or full-off) system. In all flights the elevons and rudder were applied simultaneously for the lateral control. The control travels from the trim positions were +-70degrees elevons, =-50 elevons for the longitudinal control, and =-10degrees for lateral control. The lifter coefficient range is from 0.56 to 0.75 and the angle of attack range is from 19degrees to 32degrees. The stability and contr! Free Flight Tunnel Tests, Consol.-Vultee XP-92 Airplane 16mm, Black & White, Silent Flight tests were made in the free-flight tunnel of the 1/20-scale model of the consolidated XB-53 airplane with flaps retracted or extended 30-degrees; inboard leading-edge slats extended or retracted; vertical tail extension or design vertical tail on; aileron and rudder or aileron only control; 40-degrees up only aileron deflection; 7-degrees or 18-degrees rudder travel;over a lift coefficient range from 0.50 to 0.95. Flight conditions are generally satisfactory, although adverse yawing is apparent and in some case the model stalls and crashes. Free Flight Tunnel Tests, McDonnell XP-88 A8irplane, 400 1947 16mm, Black & White, Silent Power-off stability and control tests of a 1/10-scale model of the McDonnell XP-88 airplane were conducted in the free-flight tunnel at the request of the Air Material Command, Army Air Forces. All flights were made with C.G. at 0.22 MAC, intake duct fairing, conventional tail, and correct scaled-down moments of inertia. Tests were made using coordinated aileron and rudder control or ailerons alone for control; with stall- control vanes off or on flaps up or trailing-edge flaps deflected 50degrees; with light wing loading of approximately 21 lbs/esq. or scaled-up wing loadings of 47.2 or 43.8 lbs./sq.ft.; with and without wing tip tanks; over a lift coefficient rang from 0.66 to 1.24. In some test condition the stability and control were satisfactory, whereas in other considerable rolling and yawing motions were apparent causing unsatisfactory stability and control. Free Flight Tunnel Tow Tests F84E 16mm, Silent, Black & White, 465ft., 13min. Free Flight Tunnel Tow Tests Model F7U-3 16mm, Silent, Black & White, 6min., 215ft. Free Spinning Tunnel Test of Some Recoveries by Firing Rockets on a 1/25-Scale Model of the Chance Vought XF8U-1 Airplane 16mm, Silent, Black & White Free-Flight Investigation of the Deployment, Dynamic Stability and Control Characteristics of a 1/12-Scale Dynamic Radio Controlled Model of a Large Booster and Parawing. 1963 16mm, Silent, Color, 400ft, 16.5min. Free-Flight Tests of a 1/15-Scale Model of the Convair XB-58 Airplane in the Langley Full-Scale Tunnel 16mm, Silent, Black & White, 200ft., 8min. Free-Flight Tunnel 1/24-Scale Model; FFT Simulated Action Shots 16mm Free-Flight Tunnel Convair XFy-1 in Take-Off, Landing, Hovering and Low Forward Speed Phases of Flight 16mm Free-Flight Tunnel Nose Jettison Tests of a 1/50-scale model Douglas D-558 and D558-2. 16mm Free-Flight Tunnel Records Stability and Control Tests Vertically Rising Aircraft 1950 16mm Preliminary Data Motion Picture Records of Stability and Control Tests of a Vertically Rising Aircraft Model in the Langley Hovering Model Flight Test Area. Tests Conducted from 1-1050 to 3-1-50. Free-Flight Tunnel Stability and Control Tests-- Straight Wing Vertically Rising Airplane; Take-Off, Landing and Hovering Flight 16mm, Silent, Color Free-Flight Tunnel Tailless Airplane, Consolidated Vultee 1944 16mm Flight tests were made in the free-flight tunnel on a 1/30 scale model of the Consolidated-Vultee Tailless airplane. Tests were made with and without slats; with vertical tail surfaces; with no propellers or propellers windmilling. In the flaps down condition, extensible horizontal tail surfaces appear, but they form part of the trailing edge of the wing in flaps up condition. Spin tests of the tailless airplane and conventional airplane are presented. Free-Flight Tunnel V-173 Vought-Sikorsky 16mm Free-Flight Tunnel XP-56 Northrop 1941 16mm Flight tests were made in the free-flight tunnel on a model of the Northrop P-56, which is a tailless airplane using upper and lower vertical tail surfaces and counter-rotating pusher type propellers. The C.G. is located at 18.1%, 20.6%, or 19.5% MAC; radii of gyration correct or 18% high; wing loading about 40% low; propellers off or windmilling; original lower fin and larger upper fin on, original lower fin on, modified upper and lower fins on, upper fin removed, or both fins removed. Stability in all cases seemed satisfactory. Friendship 7 16mm FST Brewster Airflows 16mm Tests to determine, by use of tufts, the air flow over Brewster F2A-1 Airplane in the full-scale tunnel with air speed at 60 MPH and the airplane in high speed attitude. Flow was steady over most of the fuselage with slight oscillating flow at forward edge of windshield and turbulent wake behind exhaust stacks. Turbulent and reversed flow appeared in rear of carburetor air intake scoop and gun blast tube openings. FST F3F-2 1938 16mm Tests were made to determine by the use of tufts the air flow and the effects of slipstream and fairings on the airflow over the F3F-2 airplane in the full-scale tunnel. The flow was reversed behind the blast tube openings and turbulent behind the exhaust stack and wheel when propeller was off. When the fuselage was refaired, blast tube openings closed, flame arrester faired and power off, the flow was smooth. FST F4F-2 1938 16mm Presents air flow over the F4F-2 airplane, by means of tufts, the full-scale tunnel. The airplane was tests with and without a propeller, with and without power, and with flaps up and down. The flow was found to be improved by propeller operation as compared with power off. Tests made after repairing the carburetor intake scoops and nose of cowling give improved flow. At angle of attack of 16.3-degrees, just beyond the maximum lift, the major part of the left wing was stalled, but the right wing was not stalled. At angle of attack of 19.5-degrees both wings were stalled. With the propeller off the area at the top of the carburetor intake scoop and at the oil cooler exhaust was stalled at the angle of attack of -1-degree. The angle of attack range for the test was from -1degree to 19.5-degree. FST Model 16mm FST P-55 16mm FST Presentation for VIC 16mm, Silent, Color FST SB2U-1 16mm FST XP2M-1 1940 16mm Tuft tests were made in the full-scale tunnel to study flow over 1/5 scale model of XPB2M1 Seaplane. Tests were made at 60 and 100 MPH air speeds; flaps up and down; power off and on; angle of attack range from -3.6-degrees to 11.2-degrees; lift coefficient of 0.7. Slow motion pictures are shown of fluid flow from dump valve outlet with outlet flush behind wing step; 45-degree extension 9.6 in. long, aft of step; 45-degree extension 7.6 ft. long, ahead of step; 45-degree extension 9.6 in. long ahead of step. FST XP-59A Fire Views of the XP-59A Fire in the Full Scale Tunnel. 16mm FST XPB2M1 16mm FST XPB2M-1 16mm FST XPB2M-1 16mm FST XTBF-1 Tufts 16mm Drag clean-up investigations were made by use of tufts to observe flow over a TBF-1 airplane in the full-scale tunnel. The effect of open and closed cowl flaps on the flow over the oil cooler exit in open and closed positions, exhaust stack, fuselage aft of turret, wing-fuselage juncture, and turret gun position was studied at angles of attack 0.1-degree and 6.5-degree FST Y03-1A Tufts* 16mm Full Scale Crash Test of a CH-47C Helicopter 1977 16mm, Silent, Color, 6.5min. Full Scale Dynamic Landing Impact Investigation of a Prototype Lunar Module Landing Gear 1969 16mm, Silent, Color, 360ft., 10min. Full Scale Res. Div. 1951 Inspection 1951 16mm, Silent, Black & White Full Scale Tunnel XP-39 1939 16mm Presents tuft studies to depict stall on a P-39 airplane in the full-scale tunnel. The tests were run at angles of attack ranging from 0-degree to 19-degree. Tuft studies showing air flow and stall over wings, fuselage, tail surfaces and duct inlets and outlets, oil cooler and fillets with wing flaps up. Gives progression of wing stall with wing flaps down; also shows air flow over supercharger. FX-12 19' P.T. Part II 1946 16mm, Silent, Black & White Preliminary Data Film for the Air Technical Services Command Stall studies were made by means of tufts in the 19 ft. pressure tunnel on the 1/8.33 Scale Model of the Republic XF-12 to ascertain the stall progression on the complete model with the NACA wing duct inlets No. 5. The tests were made with the propellers removed; all control surfaces neutral; with and without nacelle cowl inlets sealed; with flaps retracted an deflected 65-degrees; with 0.50 and 0.75 rated power; thrust coefficient of 0; for RN's ranging from 2,330,000 to 3,420,000; Mach numbers of 0.09 and 0.13; over an angle of attack range from 2.3-degrees to 20.4-degrees; and a lift coefficient range from 0.26 to 3.03. General Electric Mark II Data Capsule 1959 16mm, Silent, Black & White, 835ft., 23min. General Electric Mark II Data Capsule 1959 16mm, Silent, Black & White, 585ft., 16min. General Electric Mark II Data Capsule 1959 16mm, Silent, Black & White, 1000ft., 28min. General Electric Mark II Data Capsule 1959 16mm, Silent, Black & White, 900ft., 25min. General Film #1 16mm, Silent, Black & White General Film #2 16mm, Silent, Black & White General Views of Goodyear Inflatoplane Mounted in the Langley Full-Scale Tunnel 1957 16mm, Silent, Black & White, 95ft. 2.5min. German Flutter 16mm Ground Vibrations Tests of the XH-17 Dynamic Helicopter Model 1960 16mm, Silent, Black & White, 950ft., 26.5min Ground Wind Models of Launch Vehicles in Langley Transonic Dynamics Tunnel 1964 16mm, Silent, Color, 115ft., 3min. Grunberg Boat 1940 16mm Tank tests were made to test the arrangement of hydrofoils on a 1/8 scale model of a 55.5 ft. high speed motor launch (Grunberg type hydrofoil boat, NACA model 103-A) in Tank #1. Displacement was 131.4lbs.; hydrofoil incidence 7-degrees; initial trim, hull 0-degrees, stabilizers 4-degrees. Short accelerated runs were made in smooth water from rest to 43 fps. Rough water behavior was shown by constant speed run of 27.4fps for a short distance then decelerated to rest. The model was also accelerated from rest to 27 fps in smooth water and constant speed into rough water. Grunberg Hydrofoil System on JRF-5 Airplane--Original Edo Super Cavitating Hydrofoil 1957 16mm, Silent, Color, 305ft., 8.5min. Gust Tunnel Inspection-- 1951 1951 16mm, Silent, Black & White Half-Size Flutter Model of Canard Surface of Beech Aircraft Corporation XKD2B-1. 9 by 18 Inch Supersonic Aeroelasticity Tunnel 1960 16mm, Silent, Black & White, 130ft. 3.5min. Hard-Surface Landing of a 1/10-Scale Dynamic Model of the Dyna-Soar Vehicle 1961 16mm, Silent, Black & White, 4.26min. Hard-Surface Landing of a 1/10-Scale Dynamic Model of the Dyna-Soar Vehicle 1961 16mm, Silent, Black & White Hawk I Missile--Wing 2, Load Condition. Limit Load at t = 32 Seconds 16mm, Silent, Color, 75ft., 3min. Hazards of Tire Hydroplaning-A Sequel 1968 16mm, Sound, Color, 528ft., 14.66min. Heating and Loading Test of Hawk Wing 8 16mm, Silent, Color, 197ft., 5min. Heating and Loading Tests of Hawk Wing 2 16mm, Silent, Black & White, 271ft., 8min. Heating and Loading Tests of Hawk Wing 7 16mm, Silent, Black & White, 271ft., 8min. Heating and Loading Tests of Hawk Wing I 16mm, Silent, Color, 190ft., 5min. Heat-Transfer Tests of Winged Reentry Vehicles Mach Number 6.80, Free Stream Temperature 650-Degree Fahrenheit. 1961 16mm, Silent, Black & White, 910ft., 25min. Helicopter Blade Stall 1946 16mm, Silent, Black & White Blade stall of a helicopter rotor in forward flight as presented along with a paper entitled Blade Stall by Gustafson and Myers at the Second Annual Forum at the American Helicopter Society in Philadelphia on March 14, 1946. Helicopter Instrument Flight and Precision Maneuvers as Affected by Changes in Damping in Roll, Pitch, and Yaw. 1955 16mm, Silent, Black & White, 290ft., 8min. Helicopter Instrument Flight Program 16mm, Silent, Black & White, 550ft., 23min. Helicopter Wake Study 1963 16mm, Sound, Black & White, 620ft., 17min Helicopters 16mm This is a publicity film presenting a tour of the LAL facilities engaged in all types of helicopter research and experiment. Views of the facilities and their part in helicopter are explained. Presents views of Physical Research Division, Helicopter Tower, Low-Turbulence Tunnel, Full Scale Tunnel, Structures Research Division, Flight Research Division, Hangar, and Flight Tests of a Helicopter. Herman 16mm, Silent, Color High Altitude Flight Test of a 40-Foot Diameter (12.2 meter) Ringsail Parachute at Deployment Mach Number of 2.95 1970 Originally recorded in 16mm, Silent, Color, 115ft., 3.2min. High Altitude Flight Test of a Reefed 12.2 Meter Diameter Disk-Gap-Band Parachute with Deployment at Mach Number of 2.58 1971 Originally recorded in 16mm, Silent, Color, 180ft., 5min. HIGH ALTITUDE PARACHUTE STUDIES 1963 16mm, Color High Speed Dive Test of XP-51 16mm, Silent, Color High Speed Modion Pictures of the McDonnell Super Talos Component Flutter Tests Conducted in the Langley Unitary Plan 1960 16mm, Silent, Black & White, 27.5min. High Speed Motion Picture of the Boeing Dyna-Soar Panel Flutter Test Conducted in the Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 250ft., 7min. High Speed Motion Picture of X-15 Panel Flutter in the Langley Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 145ft., 4min. High Speed Motion Pictures of Flutter Tests of Some Oriented Skin Panels Related to the Boeing Dyna-Soar Glider 1961 16mm, Silent, Black & White, 25min High Speed Motion Pictures of NAA B-70 Panel Flutter Tests Conducted in the Langley Unitary Wind Tunnel 1961 16mm, Silent, Black & White, 710ft., 20min. High Speed Motion Pictures of the Boeing Dyna-Soar Panel Flutter Tests Conducted in the Langley Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 457ft., 13min. High Speed Motion Pictures of the Boeing Dyna-Soar Panel Flutter Tests Conducted in the Langley Unitary Wind Tunnel 1961 16mm, Silent, Black & White, 2430ft., 66min. High Speed Motion Pictures of the Project Mercury Capsule Shingle Tests Conducted in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Black & White, 475ft., 13min. High Speed Motion Pictures of the Second Phase of Flutter Test of Surfaces of the Boeing IM-99B in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Black & White, 410ft., 11.5min. High Speed Motion Pictures of the Typhoon Wind-Elevon Flutter Tests in the Langley Unitary Plan Wind Tunnel 1961 16mm, Silent, Black & White, 2380ft., 65min. High Speed Motion Pictures of the Typhoon Wind-Elevon Flutter Tests in the Langley Unitary Plan Wind Tunnel 1961 16mm, Silent, Black & White, 800ft., 23min. High Speed Schileren Movies of the Flow About a Sphere Towed at Supersonic Speed 1959 16mm, Silent, Black & White, 135ft., 3.5min. High Speed Schileren Movies of the Flow About Different Cone Models Towed at Supersonic Speeds Behind a Conical Body (4.875 Inches in Diameter) 1960 16mm, Silent, Black & White, 308ft., 8.5min. High Speed Schlieren Movies of a 1/9-Scale Model of the Samos Satellite During Dynamic Stability Tests in the Langley Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 485ft., 13.5min. High Speed Schlieren Movies of the McDonnell Typhon Flutter-Model Tests in the Langley Unitary Plan Wind Tunnel; 1960 16mm, Silent, Black & White, 360ft., 10min. High Speed Schlieren Studies of Flow Over Mercury Atlas Vehicle in the Langley 2-Foot Transonic Aeroplasticity Tunnel 1960 Originally recorded in 16mm, Silent, Black & White, 535ft., 16min. High Temperature Materials 1962 16mm, Sound, Color, 900ft., 27min. High Temperature Testing of Aircraft Structures 1958 16mm, Silent, Color 360ft., 10min. High Temperature Testing of Aircraft Structures, VPI-1961 1961 Originally recorded in 16mm, Silent, Color, 630ft., 17min. High Temperature Testing of Aircraft Structures,1961, Presented by Roger Anderson 1962 16mm, Silent, Color, 510ft., 14.5min. High-Speed Color Schileren Studied Over a Two-Dimensional Trailing Edge Flap-Type Control 1958 16mm, Silent, Color, 215ft., 6min. High-Speed Motion Pictures Taken During Flutter Tests of Fiberglass-Foam Sandwich Skin Panels Conducted in the Langley Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 160ft., 3.5min. High-Speed Schlieren Movies Made in the Langley Unitary Plan Tunnel During Test of the Drogue Parachute to be used for Stabilization of the Project Mercury Capsule 1959 16mm, Silent, Black & White, 880ft., 25min. High-Speed Schlieren Movies Made in the Unitary Plan Wind Tunnel of Hot Jets, Exhausting into a Supersonic Stream 1961 16mm, Silent, Black & White, 780ft., 21.40min. High-Speed Schlieren Movies of Decelerators at Supersonic Speeds. 1960 Originally recorded in 16mm, Silent, Black & White, 245ft., 7min. High-Speed Schlieren Movies of the Flow About Reefed Parachute Models Towed at Supersonic Speeds Behind a Conical Body (4.875 Inches in Diameter). Drag Values Based on the Unreefed Diameter of 1.73 Feet Porosity of Unreefed Parachute is 28 Percent 1960 Originally recorded in 16mm, Silent, Black & White, 550ft., 15min. High-Speed Schlieren Movies of the Stage Separation of the Martin WS-107A-2 (Titan) in the Langley Unitary Plan Wind Tunnel-- Phase II 16mm High-Speed Schlieren Studies of Flow Over a Model of the Dyna-Soar Vehicle in the Langley 2-Foot Transonic Aeroplasticity Tunnel 1960 16mm Silent, Black & White, 582ft., 12min. History of the Helicopter 16mm, Sound, Black & White HL-10 in 30x60 16mm, Silent, Black & White HL-10 Model Landing Tests Job 109 16mm, Silent, Color Hovering and Transition Flight Tests of a 1/5-Scale Model of a Jet Powered Vertical Altitude VTOL Research Airplane. 1958 16mm, Silent, Color, 550ft., 15min. An experimental investigation has been made to determine the dynamic stability and control characteristics of a 1/5-scale flying model of a jet-powered vertical-attitude VTOL research airplane in hovering and transition flight. The model was powered with either a hydrogen peroxide rocket motor or a compressed-air jet exhausting through an ejector tube to simulate the turbojet engine of the airplane. The gyroscopic effects of the engine were simulated by a flywheel driven by compressed-air jets. In hovering flight the model was controlled by jet-reaction controls which consisted of a swiveling nozzle on the main jet and a movable nozzle on each wing tip; and in forward flight the model was controlled by elevons and a rudder. If the gyroscopic effects of the jet engine were not represented, the model could be flown satisfactorily in hovering flight without any automatic stabilization devices. When the gyroscopic effects of the jet engine were represented, however, the model could not be controlled without the aid of artificial stabilizing devices because of the gyroscopic coupling of the yawing and pitching motions. The use of pitch and yaw dampers made these motions completely stable and the model could then be controlled very easily. In the transition flight tests, which were performed only with the automatic pitch and yaw dampers operating, it was found that the transition was very easy to perform either with or without the engine gyroscopic effects simulated, although the model had a tendency to fly in a rolled and sideslipped attitude at angles of attack between approximately 25 deg and 45 deg because of static directional instability in this range. Hovering Flight Investigation of Two Methods of Controlling a Man-Carrying Ducted-Fan Vehicle of the Flying-Platform Type 1961 16mm, Silent, Black & White Hovering Flight Tests of a 4 Engine Transport Vertical Take-off Airplane Model Utilizing Large Flap and Extensible Vanes for Redirecting the Propeller Slip Stream 16mm, Silent, Color, 370ft, 10min. Hovering Flight Tests of a Model of a Vertical Take-off Airplane with Tilting Wing and Props 16mm, Silent, Black & White, 200ft., 5.5min. Hovering Flight Tests of a Model of Transport Vertical Take-Off Airplane with Tilting Wing and Propellers 1956 16mm, Silent, Color, Written Narration, 200ft., 6min. Hovering Flight Tests of Ducted Fan Model 16mm, Silent, Black & White HQ - 241 ACCESS 16mm, Silent, Color Human Tolerance to Wind Blast (8' HST) 16mm, Silent, Black & White Human Tolerance to Wind Blasts 1946 16mm, Color A Navy investigation was made in the 8-Foot high-speed wind tunnel to determine human tolerance to wind blasts. Preliminary tests were made on a dummy. Tests were made on guinea pigs at Mach numbers ranging from 0.09 to 0.65. The Mach number range for the tests on human subjects was 0.04 to 0.58. Hydrodynamic Characteristics of a 1/19-Size Model of a Six-Engine Hull Type Seaplane Designed for Supersonic Flight 1958 16mm, Silent, Black & White Hydrodynamic Characteristics of a 1/8-Scale Model of the Glenn L. Martin Co. PBM-5 Seaplane Equipped with a Single Hydro-Ski. 16mm, Silent, Black & White, 380ft, 35min Hydrodynamic Characteristics of Missiles Launched Under Water 1958 16mm, Silent, Color Hydrodynamic Investigation of a Multijet Water-Based Aircraft Having Engines Exhausting From the Step--Model 333 1957 16mm, Silent, Color, 470ft., 13min. Hydrodynamic Investigation of Two Configurations for Transonic Seaplanes (Gross Weight, 160,000 lbs.) 16mm, Silent, Black & White, 140ft, 3.5min Hydrodynamic Investigation of Two Transonic Seaplane Configurations--Rough Water Taxi Test 16mm, Silent, Black & White Hydrodynamics Annual Report 1948 16mm, Sound The progress report for 1948 by the Consolidated Vultee Aircraft Corp. Shows work done with a radio controlled model of the XP5Y-1. Methods of obtaining information on the longitudinal stability and control and the spray characteristics of the model are shown, as well as, runs of the model using bang-bang or on-off controls. Also presented are catapult and towing tests of a model similar to the Skate 6. Tests are run on a miniature pulse-jet engine (Dynajet) use to power the model. Tests are run on a miniature pulse-jet engine assault transport seaplane is presented. Hydro-Ski Development 16mm, Sound This film was made by the Engineering Division at Wright-Patterson Air Force Base, showing take-off and taxiing runs of the Grumman 0A-9 amphibian with and without Edo hydro-skis. Landings with skis installed and beaching methods are also shown. Hyperbolic Velocity Reentry -Project Fire Photographic Summary and Record of Reentry Phenomena at Hyperbolic Velocities 1966 16mm, Sound, Color, 310ft., 8.5ft. Hypersonic Boost Gilder Film 1957 35mm., Silent, Black & White, 2.5min. Hypersonic Research 1957 16mm, Silent, Color, 500ft., 14min. Ice Elimination in Flight 16mm A study of the elimination of ice on airplane wings was made by mounting a section of wing on an airplane. A device to provide an atomized spray of water was placed ahead of the model wing. The tests were made at altitudes to obtain a temperature of 26-degrees F. This method used leather covering over the leading edge. Alcohol was applied under pressure to the inner surface and forced through the leather. About 40 lbs. of alcohol per hour is required to eliminate this type of ice formation on a wing of 50 ft. span. Ice formation on a propeller and its spinner is also shown. Ignition Studies of a T-22 Propellant Targets by Impact and Penetration of Steel Spheres 1961 16mm, Silent, Color, 31.5min. Illustration of Collective Effects in Stellar Dynamics 16mm, Silent, Color Impact Basin Demonstration, 1949 Annual Inspection 16mm The demonstration given by personnel of the Impact Basin showed effects of landing impact on the landing gear, wings, and fuselage of the simulated airplane. Impact on Dust Like Media 1962 16mm, Silent, Black & White, 70ft., 2min. Incipient Spin Tests of a 1/35-Scale Model of the Convair F-102A Airplane 1956 16mm, Silent, Black & White, 1070ft., 30min. Induced Flowing Ground Effect 1958 16mm, Silent Black & White 145ft., 6min. Inflation Tests in 41-Foot Vacuum Chamber of Project Able 12-Foot diameter Spherical Radar Reflector 1958 16mm, Silent, Black & White, 235ft., 6.5min. In-Flight Demonstration of Variable Wing Sweep with a Free Flying Model of Supersonic Transport Configuration. 1961 Originally recorded in 16mm, Silent, Black & White, 163ft., 4.5min. In-Flight Pictures of the Wing-Fuselage Juncture of the F8U-1 Airplane 1958 16mm, Silent, Black & White Injection, Distribution, and Evaporation of Liquids in the Flow Fields of Hypersonic Vehicles 1964 16mm, Silent, Black & White, 75ft., 2min. Inside of Arch Welding- Part 5 16mm, Silent, Black & White Installation of HL-10 Model in the Langley Research Center's Full Scale Wind Tunnel 1964 16mm, Silent, Color, 300ft., 8.5min. Integrated Flight Research Facilities of Wallops Flight Center and Langley Research Center 16mm, Sound, Color, 600ft., 14.5min. Interstage Fairing Used as a Decelerator 1961 16mm, Silent, Black & White, 370ft., 10min. Inverted Spin Tests of a 1/25-Scale Model of the Douglas F5D-1 Airplane 1955 16mm, Silent, Black & White, 710ft., 28min. Inverted Spin Tests of the 1/25-Scale Model of the McDonnell F3H-2N Airplane 1955 16mm, Silent, Black & White, 200ft., 8min. Investigation of a 0.04-Scale Pressure Model of the Martin WS-107A-2 in the Langley Unitary Plan Wind Tunnel 15mm Investigation of a 1/19-Scale Cable Mount Stability Model of the C-141 Airplane in the Langley Transonic Dynamics Tunnel 1962 Originally recorded in 16mm, Silent, Color, 355ft., 10min. Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area. Detailed Blade Element Performance 1957 16mm, Silent, Black & White Investigation of a New Technique for Releasing an Externally Carried Fuel Tank at Subsonic and Supersonic Speeds Using a 1/40-Scale Model of a Supersonic Bomber Airplane 1961 16mm, Silent, Black & White, 275ft., 20min. Investigation of a Tilting-Wing Vertical Take-Off and Landing Jet Airplane Model in Hovering and Transition Flight 1958 16mm, Silent, Color, 400ft., ll min. Investigation of Dynamic Stability and Controllability in the Langley FFT. 16mm The free-flight tunnel, of which external and sectional views are shown, is an open-return closed-throat tunnel which is housed in a metal sphere. The air is pulled through the test section by the propeller at the rear of the tunnel, which may be tilted to simulate flight path angles over a range from 40-degree glide to 15-degree climb. Two operators at the side of the tunnel control and the tunnel angle and airspeed. The pilot operates the model control remotely from his seat at the rear of the tunnel. The pilot's controls consist of a rudder-aileron stick and an elevator stick which operates electric switches, which control the current which flows through a light flexible cable of electromagnets in the model. The electromagnets are linked to the hinged control surfaces and, when the magnets are energized, the surfaces are moved. For a take-off, the tunnel angle is brought up and the airspeed increased. After take-off, the tunnel angle and airspeed are adjusted to the flight trim conditions. The model is landed by reducing the tunnel angle and airspeed. The effects of design factors on dynamic stability and control ability are illustrated by records mad of model flight tests. From theses tests the effects of dihedral and vertical tail area; reducing directional stability control with ailerons and rudder interconnected increasing dihedral; increasing dihedral and decreasing directional stability and control with ailerons alone; it was determined that low dihedral and large vertical tail are desirable. The effects of AR and sweep of the wing; Damping in roll of wing-tip tanks; and of fuel sloshing on the lateral oscillation were shown. Longitudinal stability was shown to depend chiefly on the C.G. location. Investigation of Hydro-Ski Stabilized Hydrofoil System Mounted on 1/8-Scale Model of Grumman JRF-5 Airplane 1985 16mm, Silent , Black & White, 300ft., 8.5min. Investigation of Longitudinal Stability Grunberg Hydrofoil System 16mm, Silent, Black & White Investigation of Low Subsonic Flight Characteristics of a 1/5-Scale Model of a Boeing Dyna-Soar Glider Configuration 1961 16mm, Silent, Color, 10.5min. Investigation of Low-Subsonic Flight Characteristics of a Model of a Hypersonic Boost Glide 1959 16mm, 8 minutes, 285 feet, silent, b/w Investigation of Low-Subsonic Flight Characteristics of a Model of Hypersonic Boost Glide Configuration Having a 78-Degree Delta Wing 16mm, Silent, Black & White, 285ft., 8min. An investigation of the low-subsonic stability and control characteristics of a model of a hypersonic boost-glide configuration having 78 deg. sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg. angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg. angle of attack and unstable at angles of attack of about 25 deg. and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg. angle of attack. 1959 Investigation of Slosh Anomaly in Apollo Lunar Module Propellant Gage 1970 16mm, Silent, Color, 200ft., 5.5min. Investigation of Stalling Characteristics of DC-3 Airplane 16mm,, Silent, Color, 75ft., 3min. Investigation of Surface Erosion Caused by a Vertical Jet of Cold Air 1958 16mm, Silent, Black & White, 90ft., 2.5min. Investigation of Technique for Cent. Landing Impact Test at Simulated Planetary Gravity 1971 16mm, Silent, Color, 180ft., 5min. Investigation of the Dynamic Stability of Two Towed Models of a Flat-Bottom Lifting Reentry Configuration 1965 16mm, Silent, Color, 1150ft., 32min. Investigation of the Flight Characteristics of a 1/5-Scale Model of a Dyna-Soar Glider Configuration at Low Subsonic Speeds 1962 16mm, Silent, Color, 545ft., 15min. Investigation of the Flight Characteristics of a Model of the HL-10 Manned Lifting Entry Vehicle 1966 16mm, Silent, Color, 225ft., 7min. Investigation of the Flutter Characteristics of 0.25-Scale Models of the Wing Aileron, Fin Rudder and Elevator of the Boeing IM-99-B in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Black & White, 1600ft., 88min. Investigation of the Landing Characteristics of a Re-entry Vehicle Having a Canted Multiple Air Bag Load Alleviation System 1963 Originally recorded in 16mm, Silent, Color, 110ft., 3min. Investigation of the Low Subsonic Flight Characteristics of a Model of a Flat-Top Hypersonic Boost Glide Configuration Having an Arrowhead Wing 1958 16mm, Silent, Black & White Investigation of the Low Subsonic Flight Characteristics of a Model of a Reentry Configuration Having a 75-Degree Delta Wing 1962 16mm, Silent, Black & White, 200ft., 5.5min. Investigation of the Low Subsonic Flight Characteristics of a Model of a Reentry Vehicle Having a 75-Degree Thick Flat Delta Wing and a Half Cone Fuselage 1961 16mm, Silent, Black & White, 195ft., 5.5min. Investigation of the Low Subsonic Flight Characteristics of a Model of an All-Wing Hypersonic Boost-Glide Configuration Having Very High Sweep 1960 16mm, Silent, Black & White, 175ft., 5min. Investigation of the Low Subsonic Flight Characteristics of a Supersonic Airplane Configuration Having Tail Surface Outboard of the Wing Tips 1961 16mm, Silent, Black & White, 8min. Investigation of the Low Subsonic Stability and Control Characteristics of a 1/3-Scale Free Flying Model of a Lifting Body Reentry Configuartion 1960 16mm, Silent, Black & White, 6.5min. Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane--Coord # AF-AM-15 1957 16mm, Silent, Black & White, 340ft., 9.5min. Investigation of the Low-Subsonic Stability and Control Characteristics of a Free-Flying Model of a thick 70-Degree Delta Reentry Configuration 1961 Originally recorded in 16mm, Silent, Black & White 196ft., 6.5min Investigation of the Skid Rocker Landing Characteristics of Spacecraft Models 1962 16mm, Silent, Color, 270ft., 7.5min. Investigation of the Subsonic and Supersonic Release Characteristics of an Externally Carried Fuel Tank From a 1/40-Scale Model of a Bomber Airplane (Phase 2); 1959 16mm, Silent, Black & White, 490ft., 26min. Investigation of the Subsonic and Supersonic Release Characteristics of an Externally Carried Fuel Tank from a 1/40-Scale Model of a Bomber Airplane (Phase 1) 1959 16mm, Silent, Black and White, 415, 11.5min. Release and flight characteristics study for externally carried fuel tank models of various configurations at subsonic and supersonic speeds Investigation of the Subsonic Stability and Control Characteristics of a 0.34-Scale Free Flying Model of a Modified Half Cone Reentry Vehicle 1961 16mm, Silent, Black & White, 230ft., 6.5min. Investigation of the Subsonic Stability and Control Characteristics of a 1/17-Scale Model of the North American X-15 Airplane with and without Fuselage Forebody Strakes 1958 16mm, Silent, Black & White, 605ft., 17min. Investigation of Underwater Launching of a Model of an Air Missile 1960 16mm, Silent, Color, 90ft., 2.25min. Investigation of Water-Pond Arresting of a Dynamic Model of a Jet Transport 1960 16mm, Silent, Color, 204ft., 5.5min. Brief dynamic-model tests have been made at the request of the Federal Aviation Agency to investigate the use of a shallow pond of water at the end of a runway as a means of arresting jet-transport aircraft when they are forced to abort on take-off or overrun on landing. Such a scheme is of particular interest for civil aircraft because it requires no modifications or attachments to the airplane and no mechanical devices in the arresting system. A modification of this scheme that uses a flexible plastic cover over the water surface has also been tested. The purpose of this paper is to present the results of a dynamic model investigation which would aid in determining whether the water-pond arresting system could be used as a means of arresting airplane overrun. Investigation of X-15 Airplane Horizontal-Tail Transonic Flutter Models in Langley Transonic Blowdown Tunnel 1959 16mm, Silent, Black & White, 400ft., 11min. Investigation of X-15 Airplane Proposed. Horizontal-Tail Transonic Flutter Models in Langley Transonic Blowdown Tunnel 16mm Investigation to Determine Conditions Under Which Downwash from VTOL Aircraft Will Start Surface Erosion for Various Types of Terrain 1959 16mm, Silent, Color, 975ft., 27min. Involuntary Eye Motions During and Nystagmus After Head Motions in a Vehicle Simulator 1967 16mm, Silent, Black & White, 110ft., 3min. J-2 in flight 16mm, Silent, Color Jet Effects on Transonic Flow Over a 16-Degree Conical Afterbody 1957 16mm, Silent, Color, 190ft., 5min Jet Shoes - A Extra-Vehicular Device 1966 16mm, Silent, Color, 200ft., 5.5min. JetShoes- an Extravehicular Space Locomotion Device 1967 16mm, Silent, Color, 440ft., 12min. JRF-5 and Bomber--Mr. Parkinson's Talk Seaplane Subcommittee Meeting January 1958 1958 16mm, Silent, Black & White, 145ft., 4min JRM-1 Flying Boat Model 164F and 164H 1943 16mm Tank tests were made in Tank # 1 for the purpose of obtaining spray pictures of 1/12-scale models of Martin JRM-1 (NACA 164). Model 164-R had design forebody. Model 164H had gradual increase in plan form forward of step to maximum of 2.74 in. at station 7.5; horizontal C.G. 30% MAC.; flap deflection 30-degrees; depth of step 0.625 in.; step 48.16 in. aft of bow; and C.G. 14.75 in., above keel at step. Both models were tested at gross loads of 82.5 and 91 lbs.; full power; propellers idling; and elevators neutural or up 9-25-degrees). JRM-1 Flying Boat Model 164J-1 1944 16mm Tank tests were made in tank #1 for the purpose of obtaining spray pictures of the 1/12-scale model of the Martin JRM-1, NACA model 164J-1, with outboard spray strips; depth of step, 0.625in.; step 48.16in. aft of bow; C.G. 14.75 in. above keel at step and 30% MAC horizontally; gross loads of 82.5, 91, and 99.5 lbs.; full power or propellers idling; and elevators neutral or up (-25-degrees). L4-4428 Ram C-C Scout S-171C 16mm, Silent, Color Laboratory Ceramic Heated Jet 1957 16mm, Silent, Color, 145ft., 4min Laboratory Conditions 16mm, Silent, Black & White Laboratory Operations Support 16mm, Sound, Color LAL Awarded Minute Man Flag 16mm, Silent, Black & White Landing and Taxiing Tests of an F-94C Nose Landing Gear Over Various Types of Runway Lights 1957 16mm, Silent, Black & White, 1210ft., 33min. Landing Characteristics and Flotation Properties of a Reentry Capsule 1960 16mm., Silent Color, 275ft., 7min. As a part of a program to investigate the landing impact characteristics of conical reentry capsules, some tests have been reported in references 1 and 2. Further experimental investigations have been made to determine the rigid-body impact accelerations of a reentry capsule having the same spherical impact surface as the Mercury capsule and are reported herein. The current investigation was made to determine impact accelerations with landings on sand and on water after a simulated parachute-supported let down. The flotation properties of the capsule also have been determined. All tests were made with 1/6-scale dynamically similar models of the Mercury reentry capsule. The landing tests were made at various flight paths to simulate the effect of surface winds that might act on the parachute-capsule combination during letdown. A range of contact attitudes was investigated to simulate the various landing attitudes that might occur if the capsule were swinging under the parachute. The accelerations were measured at the center of gravity of the capsule and for some tests the accelerations were measured at offset positions corresponding to those a man's head might have in the manned capsule. The flotation properties of the capsule were investigated at various center-of-gravity locations. Tests were also made to determine the effect on the flotation properties of flooding the space between the passenger's compartment and the heat shield of the capsule. The effects of a man with his survival equipment making an exit through the canister were also determined. All values and measurements in the paper are given full scale. Landing Characteristics of a Dynamic Model of the HL-10 Manned Lifting Entry Vehicle 1966 16mm, Silent, Color, 495ft., 14min. Landing Characteristics of a Re-entry Vehicle with a Passive Landing System for Impact Alleiviation 1963 Originally recorded in 16mm, Silent, Color, 180ft., 5min. Landing Characteristics of a Ventricular Shaped Reentry Vehicle 1961 16mm, Silent, Color, 260ft., 7min Landing Characteristics of a Winged Reentry Vehicle with All Skid Landing Gear Having Yielding Metal Shock Absorbers. 1962 Originally recorded in 16mm, Silent, Color, 270ft., 7.5min Landing Characteristics of the Apollo Spacecraft with Deployed Heat Shield Impact Attenuation Systems 1965 Originally recorded in 16mm, Silent, Color, 580ft., 16min. Landing Energy Dissipation for Manned Reentry Vehicles 1960 Originally recorded in 16mm, Silent, Color, 128ft., 3.5min. Analytical and experimental investigations have been made to determine the landing-energy-dissipation characteristics for several types of landing gear for manned reentry vehicles. The landing vehicles are considered in two categories: those having essentially vertical-descent paths, the parachute-supported vehicles, and those having essentially horizontal paths, the lifting vehicles. The energy-dissipation devices discussed are crushable materials such as foamed plastics and honeycomb for internal application in couch-support systems, yielding metal elements as part of the structure of capsules or as alternates for oleos in landing-gear struts, inflatable bags, braking rockets, and shaped surfaces for water impact. It appears feasible to readily evaluate landing-gear systems for internal or external application in hard-surface or water landings by using computational procedures and free-body landing techniques with dynamic models. The systems investigated have shown very interesting energy-dissipation characteristics over a considerable range of landing parameters. Acceptable gear can be developed along lines similar to those presented if stroke requirements and human-tolerance limits are considered. Landing Impact and Braked Taxi Tests on Various Types of Metal Landing Mats and Membranes 1959 16mm, Silent, Black & White, 885ft., 24.5min. Landing Impact Dissipation Systems 1961 Originally recorded in 16mm, Silent, Color 150ft., 4min. Landing Impact Studies of a 0.3-Scale Model Air Landing System for a Navy Fighter Airplane 1975 16mm, Silent, Color, 8.5min. Landing Investigation of Panto Base Version C-123--Part I. 16mm, 290ft, 8min Landing Loads Track 1957 16mm, Silent, Color, 204ft., 6.5min Landing Loads Track 1966 16mm, Sound, Color, 180ft., 5min. Landing Loads Track 16mm, Sound, Color Landing Loads Track Propulsion Model Tests 16mm, Silent, Black & White Landing Loads Track Test of Titanium Landing Gear Skid 1959 16mm, Silent, Black & White, 30ft., 1min. Landing of Manned Reentry Vehicles 1960 Originally recorded in16mm, Silent, Color, 130ft., 4min. Landing Performance of an Air Cushion Landing System Installed in a 1/10-Scale Dynamic Model of the C-8 Buffalo Airplane 1973 16mm, Silent, Color, 4min. Landing Practices of General Avaition Pilots in Single Engine Light Aircraft 16mm, Color, 400ft., 4.5min Landing Tests DR-77 With and Without Shock-Absorber Ski Struts 16mm, Silent, Color, 215ft, 6min Landing-Impact characteristics of Lead-Alleviating Structs on a Model of Winged Space Vehicle. 1960 16mm, Silent, Black & White, 109ft., 3min. A brief experimental investigation was made of the landing-impact characteristics of a 1/9-scale dynamic model of a winged space vehicle. The landing tests were made by catapulting a free model onto a hard; surface runway and onto water. The model had a conical fuselage and a flat - plate wing with a basic delta planform and 75 deg sweepback of the leading edge. The use of yielding-metal shock absorbers and various landing-gear arrangements was investigated during landing impact. The basic landing gear consisted of a dual rubber-tired nose wheel and twin main skids aft of the center of gravity near the wing tips. landing motion and acceleration data were obtained over a range of landing attitudes, gross weights, and initial sinking speeds. Brief tests were made with an alternate nose-wheel location. An all-skid configuration also was briefly evaluated for hard-surface and water landings. The landing gear employing yielding struts for impact-energy absorption during hard-surface landings resulted in accelerations of approximately 5 1/2 g near the nose gear over a range of landing parameters. Replacing the nose wheel and tire with a skid did not significantly change the accelerations. Landings in smooth water with rigid struts and adequate planning area at the nose skid resulted in a maximum landing acceleration of approximately 4g. Langley Control-Line Facility 1957 16mm, Silent, Color, 175ft., 5min. Langley Film for Ames Inspection 1958 16mm, Color, 367ft., 12min. Carry loads, aerodynamic interference effects and drop characteristics of x-15 through b-52 flow field Langley Free-Flight Tunnel Film Record of Flight Tests of a Model Similar to the 1/10 Scale model of the Douglas XS-3 Airplane 1949 16mm Langley Interactive Computerized Circuit-Analysis (LICCA) Capability 1971 16mm, Silent, Color, 1045ft., 29min. Langley Research Center Vortex Research 1974 16mm, Sound, Color, 11.20min. Langley Research Center's Weightlessness Simulator Emergency Water Dumping 1959 16mm, Silent, Black & White, 80ft., 2min. Langley Tank Model 384 1959 16mm, Silent, Color, 200ft., 5.5min Large Angle Motion Test, Including Spins for a Free Flying Dynamically Scale Radio Controlled 1/9-Scale Model of an Attack Airplane 1961 16mm, Silent, Color, 549ft., 15min. Large Angle Motion Tests, Including Spins of a Free-Flying Radio Controlled Model of a Twin Jet Swept Wing Fighter Airplane 1960 16mm, Silent, Color Lass Inflate 16mm, Silent, Color Lateral-Directional Characteristics of a 1/10-Scale Model Variable Sweep Fighter Airplane at High Angles of Attack--Coord # N-AM-154 1972 16mm, Silent, Color, 6min. Launch Vehicle Dynamics Demonstrator Model 1963 Originally recorded in 16mm, Silent, Color, 125ft., 3.5min. Launching and Tracking Movies of Hurricane Model B120-2673 Launched from Wallops Island, Va on August 11, 1958 at 0923 e.s.t. 1958 16mm, Silent, Color, 7min. Lecture Film Showing Hydrodynamics Division Facilities and Typical Research Projects 1959 16mm, Silent, Color, 315ft., 8.5min. Lewis Fim, Wright Lecture, 1939 1939 16mm, Silent, Black & White Light Airplane Crash Tests at Three Flight Path Angles 1978 16mm, Sound, Color, 11min. Light Airplane Crash Tests at Three Pitch Angles 1979 16mm, Silent, Color, 400ft., 9.5min. Light Airplane Crash Tests at Three Roll Angles 1979 16mm, Sound, Color, 9.5min. Listening Tests of Modified De Havilland ""Otter"" Airplane 1957 16mm, Silent, Black & White, 815ft., 24min. Little Joe 1960 16mm, Sound, Color, 1040ft., 28.5min. Little Joe Support. Langley Inspection, 1959 1960 16mm, Silent, Black & White, 360 ft., 10 min. Load Alleviating Effects of Hydro-Skis on High Wing Loading Model 16mm, Silent, Color, 67ft, 2.75min Load Test of Northrop Hawk Wing 8 at Room Temperature 1956 16mm, Silent, Black & White, 110ft., 4.5min. Low Speed Aircraft (1974 Inspection Film) 16mm, Sound, Color, 700ft., 19.5min. Low Speed Deployment, Inflation, and Steady Descent Characteristics of Ram-Air-Inflated Balloon Recovery Systems with Peripheral Airscoops 1969 16mm, Silent, Black & White, 185ft., 5min. Low Speed Dynamic Model Investigation of Apollo Command Module Configuration in Langley Spin Tunnel 1964 16mm, Silent, Color, 490ft., 13.5min. Low Speed Dynamic Model Investigation of Apollo Command Module Configuration in the Langley Spin Tunnel 1967 Originally recorded in 16mm, Silent, Black & White, 165ft., 4.5min. Low Speed Flight Characteristics of a Variable-Wing-0-Sweep fighter Model 1964 16mm, Silent, Color Low Speed Flight Tests of Three Hypersonic Boost-Glide Airplane Model 1957 16mm, Silent, Black & White, 225ft., 6.25min. Low Speed Force and Flight Investigation of a Model of a Modified Parawing Utility Vehicle 1964 16mm, Silent, Color, 220ft., 6min. Low Speed Force and Flight Investigation of Various Methods for Controlling Parawings 1956 16mm, Silent, Color, 10ft., 4min. Low Speed Free-Flight Stability and Drag Characteristics of Radically Vented Parachutes 1964 16mm, Silent, Color, 310ft., 8.5min. Low Speed Wind Tunnel Investigation to Determine the Flight Characteristics of a Model of a Parawing Utility Vehicle 1962 16mm, Silent, Black & White, 250ft., 7min. Low Subsonic Flight and Force investigation of a Supersonic Transport Model with a Double Delta-Wing 1967 16mm, Silent, Color, 150ft., 4min. Low Subsonic Flight and Force Investigation of a Supersonic Transport Model with a Variable Sweep Wing 1968 16mm, Silent, Color, 260ft., 7min. Low Subsonic Flight and Force investigation of a Supersonic Transport Model with Highly Swept Arrow Wing 1967 16mm, Silent, Color, 240ft., 6.5min. Low Subsonic Flight Characteristics of a Model of a Supersonic Airplane Configuration With a Parawing as a Landing Aid 1963 16mm, Silent, Black & White, 158ft., 5min. Low-Subsonic Wind Tunnel and Free-Flight Drop Test Investigation of a Paraglider Configuration Having Large Tapered Leading Edges and Keel 1966 16mm, Silent, Color, 320ft., 9min. Lunar Landing Characteristics of a Lunar Excursion Module Having Various Multiple-Leg Landing-Gear Configurations 1963 Originally recorded in 16mm, Silent, Color, 560ft., 15.5min. Lunar Orbiter (Shortened version) 1964 16mm, Sound, Color, 925ft., 26min. Lunar Program Quarterly Report Number 5 1962 16mm, Sound, Color, 390ft., 11min. Man in Flight 16mm, Silent, Color Man Loads 30 Cell Manometer 16mm Man\Computer Interface 16mm, Silent, Color Martin DS-1 Wing Flutter Model 16mm, Silent, Black & White Martin DS-1 Wing Flutter Model 1959 16mm Mastery of Space 16mm, Sound, Color, 58min. Mastin DS-1 Model 1A 8-Inch Hat- Test 4-Run 2 16mm, Silent, Black & White Materials Tests in Co-operation With U.S. Navy Polaris Project at Langley 11-Inch Ceramic-Heated Tunnel 1960 16mm, Silent, Color 575ft., 16min Materials Tests in Electric Arc-Powered Air Jet 1957 16mm, Silent, Color 438ft., 12min. Materials Tests in Langley 11-Inch Ceramic Heated Tunnel 1960 16mm, Silent, Color 80ft., 2min. Mechanical Analogy of the Effect of Fuel Sloshing on Missile Stability 1959 16mm, Silent, Color, 107ft., 3min. Medical Monitoring in Flight 1966 16mm, Sound, Color, 350ft., 10min. Melting of Missiles 16mm Melting of Models by Aerodynamic Heating in the Langley 11-Inch Hypersonic Tunnel 16mm, Silent, Black & White Message to Employees of NACA 1958 16mm, Sound, Black & White, 11min. Method of Control Operation of a 1/25-Scale Free Flying Model of a Boeing Dyna-Soar Configuration 1961 16mm, Silent, Black & White Methods and Materials Used in Model Construction at Langley Laboratory (T.F. no.27) (no.579) 16mm, Color, Sound, 950ft., 26min. Micrometeroid Satellite S-55 Separation Environment and Spin Tests 1961 16mm, Silent, Black & White, 385ft., 11min. Mobile Work Station Concept Mechanically Aided Astronaut Assembly of Large Space Trusses 1983 16mm, Silent, Color, 250ft., 7min. Model 203 A Spray Characteristics w/full Power 16mm, Silent, Black & White Spray characteristics tests were made in Tank #1 of a 1/10-scale powered dynamic model (NACA 203A) with a hull having a length-beam ratio of 9.0. Take-off runs were made with full power at acceleration 1 ft./sec [2nd power]., flaps done 20-degrees, elevators up 10-degrees, for gross loads of 72,000, 82,000, and 92,000 lbs. Model 206 Rough Water 16mm, Silent, Black & White Taxying, take off, and landing runs in rough water and landing runs in smooth water for comparison purposes were made in Tank #1 on a 1/11-scale dynamic model of the Bureau of Aeronautics design no. 22ADR, class VPB airplane, NACA model 206. Taxying runs were made in 6in. x 10 ft. waves with flap deflection 20-degrees, stabilizer setting -9.5-degrees to wing, C.G. at 24% MAC, gross load 78.1 lb., top speed of 18 fps and acceleration of 0.6 ft/sec. [2nd power]. Take off runs were made in the same waves at acceleration of 2.0 ft/sec [2nd power]. Landings were made in the same waves at carriage deceleration of 2.0 ft/sec [2nd power], and trim angles ranging from 14-degrees to 4-degrees. Smooth water landings were made at trim angles from 13-degrees to 3 1/2-degrees. Model 228 Preliminary Data Film 1974 16mm, Silent, Black & White Take-off and landing tests were made in Tank #1 on a 1/10 scale model of a long range, high-speed flying boat with hull length-beam ratio of 10.0. The model of the Consolidated Vultee P5Y-1 (NACA 228J-1) had a short, constant-dead-rise afterbody; gross load of 132.5 lb.; step 16.2% beam deep at keel, and 14.8% beam deep at centroid; and an angle of afterbody keel of 4.5-degrees. Test conditions for take-off were: flaps deflected 20-degrees, C.G. at 30% MAC; acceleration of 4.5 ft./sec [2nd power]; full power, 46.6 lb. static thrust; range of elevator deflections from -15-degrees to 0-degrees; range of hump trim angles from 9.0-degrees to 10.0-degrees; and take-off trim angles of 5.0-degrees and 7.5-degrees. The model porpoised 2.5-degrees (from 7.5 to 10) just before take-off. The test conditions for landing were: flaps deflected 50-degrees; C.G. at 34% MAC; deceleration of 2.0 ft./sec [2nd power].; 1/4 power, 11.6 lbs. static thrust; elevator deflection constant after initial contact; range of landing trim angles from 4.3-degrees to 11.5-degrees; range of landing speeds from 58 to 48 fps. Of the three landings shown, 2 were unstable and the other was stable. Model Bomb Releases at Supersonic Speeds 16mm, Silent, Black & White Model Ditching Bomber Equipped with Hydro-Skis 16mm, Silent, Black & White Model Investigation of Technique for Full Scale Landing Impact Tests at Simulated Lunar Gravity 1965 Originally recorded in 16mm, Silent, Color, 147ft., 4min. Model Rotor Dust Flow 16mm Model Test of Mars Entry Vehicles in Langley Spin Tunnel 1964 Originally recorded in 16mm, Silent, Black & White, 120ft., 3.5min Model Wind Tunnel and Flight Investigation of a Parawing Lifting Body Landing System 1970 16mm, Silent, Color, 550ft., 15.15min. Models Tank 1, 203, 213, and 214 1946 16mm, Silent, Color Spray characteristics tests were made in smooth water in tank #1 at loads of 75,000 and 95,000 lbs. on the powered dynamic models which represent alternate designs for a twin-engine flying boat similar to the Boeing XPBB-1. The length beam ratios of the hulls are: for model 213, 1/b=6.0 for model 203, 1/b=9.0; for model 214, 1/b=12.0. The mean acceleration is 2 ft./sec [2nd power]. Mosquito Spray: Chincoteague 16mm, Silent, Color-Black & White Motion Picture Supplementing Talk by A.I. Nielhouse on Special Problems of Spin Research 1959 16mm, Silent, Black & White, 400ft., 11min. Motion Pictures of the 0.10-Scale Model of the Boeing Dyna-Soar Glider Taken in the Langley Unitary Plan Wind Tunnel 16mm, Silent, Black & White Motion Pictures of the Boeing Dyna-Soar Panel Flutter tests Conducted in the Langley Unitary Plan Wind Tunnel Parts I & II Originally recorded in 16mm, Silent, Black & White, 535ft., 15min. Motion Pictures Supplementary to Tests of a 1/4-Scale Model of the Beech XKD2B-1 Target in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Color, 380ft., 10.5 Motion Pictures Supplementing Talk by A.I. Neihouse on Design and Operating Techniques of Vertical Spin Tunnels. 16mm, Silent, Black & White, 340ft., 14min. Motion Simulator Test 16mm, Silent, Black & White Motion Simulator Test 16mm, Silent, Black & White Motion Simulator Tests 16mm, Silent, Black & White Motion Simulator Tests 16mm, Silent, Black & White Movies Made in the Unitary Plan Wind Tunnel of the Goodyear Aircraft Corporation Inflatable Decelerator Towed at Supersonic Speeds 1961 Originally recorded in 16mm, Silent, Black & White, 663ft, 18.5min. Movies of Goodyear Corporation's Inflatable Decelerators Towed at Supersonic Speeds Behind a Cylindrical Body 2.400-Inches in Diameter in the Unitary Plan Wind Tunnel 1962 16mm, Silent, Black & White, 625ft., 18min. Movies of the Goodyear Aircraft Corporation Balloon in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Black & White, 160ft., 4min. Movies of the Goodyear Aircraft Corporation Inflatable Decelerators Towed at Supersonic Speeds Behind a Conical Body 2.400 Inches in Diameter in the Unitary Plan Wind Tunnel 1961 Originally recorded in 16mm, Silent, Black & White, 940ft., 26min. Movies of the Martin Aircraft Company Parachute and Balloon Decelerators Towed at Supersonic Speeds Behind an Unsymmetrical Reentry Body (4.80-Inches in Length) in the Unitary Wind Tunnel 1961 16mm, Silent, Black & White, 35mm Movies of the Martin Parachute and Balloon Decelerators Towed at Supersonic Speeds Behind an Unsymmetrical Reentry Body in the 8-Foot Transonic Pressure Wind Tunnel 1961 16mm, Silent, Black & White,1610ft., 44.5min. MR-3 Board Pilot Observer Film 1962 16mm, Sound, Color, 800ft., 21min. Mruoc-X-1, D-558, X-4 16mm, Silent, Color N. A. A. FJ-2 Spoiler Aileron Tuft Studies 16mm, Silent, Black & White NACA Corner Reflector Satellite 1957 16mm, Silent, color, 400ft., 11min. Film shows infloation of 4-Foot diameter model and 12-Foot diameter models; methods of folding model. NACA Five-Stage Solid Rocket 1958 16mm, Silent, Black & White, 562ft., 16min. NACA High Speed Flight Research Station 16mm, Color NACA Research 16mm, Sound NACA Research 16mm NACA Research on VTOL and STOL Airplanes. 1957 16mm, Silent, Color, 990ft., 25min. NACA Sub-Committee Meeting on Fluid Mechanics. NACA Three-Stage Hypersonic Test Vehicle 16mm, Silent, Black & White, 250ft, 11min NACA Subsatellites 1957 16mm, Silent, Black & White, 141ft., 4min. NACA Tank Test Model #133 1942 16mm, Silent, Black & White NASA Friction Treadmill 1959 16mm, Silent, Black & White, 45ft., 1min. NASA Landing Loads Track Tests of Landing Gear Skids and Wheels 1959 16mm, Silent, Black & White, 4000ft., 1hr. 50min. NASA Projects 16mm, Silent, Black & White NASA Roundtable Scientists Discuss the Moon 1962 16mm, Soung, Black & White, 685ft., 19min. NASA/DOD UKx4 Scout Calif. Boy Scouts 16mm, Silent, Color, 325ft Natural Antisymmetric Mode Shapes of Liquids in Containers of Various Shapes 1961 16mm, Silent, Color, 545ft., 15min. Navy Ditching Tests SB2C-1 Airplane 16mm, Silent, Black & White Ditching tests were made using the seaway catapult at Langley Field, VA., on a 1/8-scale model of the SB2C-1 airplane with normal gross weight of 13,060 lb., and C.G. of 30.2% MAC and 1.2 in. below the thrust line. The tank tests indicated a more pessimistic behavior of the airplane than the catapult tests. The principal reason for the difference in the ditching behavior was that the flaps failed completely almost every time in the catapult tests while they seldom failed in the tank tests. The more frequent flap failure in tests at the outdoor catapult may be due to the higher impact loads. Higher loads might be caused by the rougher water surface (ripples occurred even in calm water) or by the slightly higher sinking speed of the model. Tests were run in calm water, along the wave crests, across the wave crests; with flaps full up or full down; with bomb-sight doors removed or with bomb-sight doors, bomb-lever doors, bomb-bay doors removed; at attitudes of 15-degrees, 8-degrees, or 2-degrees; over an airspeed range from 58-115.6 knots. Wing low landings and dives caused by the tail of the airplane hitting the leeward side of a wave are also shown. Navy Landings and Take-offs 16mm A number of take-offs and landings of full size Navy seaplanes were made in the open sea at Langley Field. Navy Yard Explosion Tests (High-Speed) 16mm Explosion tests in the open sea were made. NB-1 Seaplane Spin Tests 16mm Depicts drop tests to determine spin characteristics of a model of the NB-1 seaplane. The model was dropped from a height of 100 feet to determine the effect of mass distribution on the spinning characteristics. The locations of weights on the model were changed along the Z axis thus affecting the moments of inertia about the X & Y axes. The center of gravity remained fixed at all times. When the weights were close to the center of gravity, the spin was flat, but when the weights were 9/12-inches from the center of gravity, the model executed a normal spin. NB-1 XF3F Flat Spins 16mm, Silent, Black & White NBC Army Hour 16mm, Silent, Black & White Nelson 16mm, Silent, Black & White Newman Research Model (In film canister with yellow Kodak Tri-X sticker on front Kodak Tri-X Reversal Safety Movie Film). 16mm, Silent, Color NGWANA BAY 16mm, Silent, Black & White Nike-Cajun (L2-379) 1960 16mm, Silent, Color, 265ft., 7min. Nike-Cajun Hurricane Photography Rocket 1956 16mm, Silent, Color, 813ft, 23min. Nike-Deacon Sounding Rocket 16mm, Silent, Color, 580ft., 24min. NOL Project Hasp 1960 16mm., Silent, Black & White, 3600ft., 1hr. 40min. Nose Blower 16mm NR79-436 Solar Flares 16mm, Silent, Color Numerical Experiments in Stellar Dynamics 16mm, Silent, Black & White Numerical Experiments with a Cylindrical Galaxy 16mm, Silent, Black & White Numerical Experiments with a Cylindrical Galaxy 16mm, Silent, Black & White Numerical Experiments with a Cylindrical Galaxy 16mm, Silent, Black & White Oblique and Yawed Landing of an F-94C Nose Gear on an Elfaka Light Unit and on Concrete 1958 16mm, Silent, Black & White, 140ft., 4min. Observation on the Flows Past Blunt Bodies at Transonic Speeds. 1959 16mm., Silent, Black & White, 325ft., 9min. Flow past low-fineness ratio blunt bodies at transonic speeds Open Throat Tunnel 16mm This film depicts smoke studies of flow in open throat tunnels. Optical Communications Device-NASA Industrial Applications Program, Langley Innovations Film Report No. 1 1962 16mm, Sound, Color, 210ft., 5.5min. Over-Water Aspects of Ground Effects Vehicles 1960 16mm, Silent, Color 175ft., 5min. P.R.T Stall Control Wing 16mm P.R.T XF4U-1 1939 16mm Investigations of air flow by means of tufts were made on a 1/2.75-scale model XF4U-1 airplane in the 20-foot propeller research tunnel. The tests were made on the model without power and powered to simulate climbing, with flaps and ailerons neutral, and with flaps down 50-degrees and ailerons dropped 10-degrees, at various angles of attack. P.R.T. Flow Over Plates 16mm P.R.T. Prop Test on Duck 16mm P.R.T. XZRS-4 16mm P.R.T. XZRS-4 16mm Ground handling tests were made in the propeller research tunnel on a model of the Goodyear-Zeppelin ZRS-4 airship (USS Akron). Forces and moments were measured over a range of angles of yaw from 0-degrees to 180-degrees. Reynolds number was 16x10-degrees. Air flow over the model was depicted by smoke. P-40 FST 16mm, Silent, Black & White, 49ft. P-40 K Tail Tufts Flight 16mm P-51D Buffeting Investigation 16mm P-66 and P-67 Tufts 16mm Tuft studies of flow over the wings, fuselage, and horizontal tail surface of the McDonnell P-67 are shown. Tests were made at the following angles of attack; 6, 8, 10, 12, 14, 16, and 18 degrees. (Note; Contrary to the title, no information on the P-66 is contained in this film) Pageos 1968 16mm, Sound, Color, 558ft., 15.5min. Panel Failure 16mm Compression tests of specimen of 245 for a Consolidated B-36. Material was artifically aged Alclad 24S-T and the stiffeners were streched 3 1/2% before aging. The stiffeners shattered at failure, at average stress of 63,130 lbs/sq.in. Parachute Recovery Tests on the 1/40-Scale Model of the B-58 Airplane 1960 16mm, Silent, Black & White, 615ft., 17min. Parachuting 16mm, Silent, Color Paraglider Deployment in the Transonic Dynamics Tunnel 1963 16mm, Silent, Black & White, 300ft., 8.5min. Paraglider Recovery System 1963 16mm, Silent, Color, 880ft., 24in. Parawing Capsule Truck Tows & Air Drops 16mm, Silent, Color, 8.5min Parawing Project Flight Tests 1968 16mm, Silent, Color, 615ft., 17min. PARD Film Used by Purser in Washington March 20, 1955 1955 16mm, Silent, Color, 285ft., 12min. PARD Inspection Film, 1956 16mm, Silent, Color, 250ft., 8min. PARD No. E119-2629 16mm, Silent, Color, 150ft., 6min. Part 1: 609-A, Blue Scout Test 3753, 24, 180 Remote 248ft, Part 2: 609-A, D-6 Flight, Blue Scout 16mm, Silent, Color Part 1: RTF X-259 Motor, S/N A3-203, QA Round Fired (#4429) 16mm, Silent, Black & White Part 1: ST-1 Tracking 16mm, Silent, Black & White Part I and II- Scout H/S Ejection A-33, S-148, Part III-6KS40 Age Life Firing, Part IV-A-62 H/S Ejection 16mm, Silent, Black & White Part I- VMSC-UK-4 Drop Test 16mm, Silent, Black & White Part I: H/S A-61 Test (SAS-A P/L) OG Part A-61C Doors Closed H/S Test, Part III: Scout Stadn. Fifth state, Dummy Sunblazer P/L Sep. Test, Part IV: A-400 Zero Separation. 16mm, Silent, Black & White Part I: IKS40 Firing w/Scout Prod. Harness, Part II: IKS75 Fir. w/Scout Production Harness, Part III: IKS40 Fir. w/Scout Shielded, Part IV: IKS40 Mtr. Harness Relocated. 16mm, Silent, Black & White Part I--Ditching Investigation of a 1/12-Scale Model of the Douglas F4D-1 Airplane 16mm, Silent, Black & White, 175ft., 7min. Part I-San Marco Despin Test, Part II- San Marco Work Print #1, Part III and IV (SM) Print Roll #2, (SM) Print Roll #1 16mm, Silent, Black & White/Color PBM-3 Spray Tests 1942 16mm, Silent, Black & White Low-speed taxying runs of a Martin PBM-3 flying boat in Hampton Roads, VA., were made at gross load of 55,000 lb., with C.G. at 29.4% MAC, and flaps down 30-degrees. Full-power acceleration and rapid deceleration runs were made with elevators neutral, full up, and full down, and slow acceleration and deceleration runs were made with elevators neutral, full up, and full down. PBN -1 Spray Characteristics 1944 16mm, Silent, Black & White Spray pictures and landing tests were made in smooth and rough water in Tank #1 on a 1/8 scale model of the PBN-1 airplane, NACA model 192. Spray pictures were made of the basic model and the model with NAF spray strips with gross load of 71.7 lbs.; stabilizer setting -2-degrees to wing chord; elevator setting 0-degrees; propeller speed, full power, 4335 RPM; propeller blade angle 17-degrees; with depths of step at keel of 3.8, degrees 7 & 10% beam; afterbody keel angles 6 1/4 degrees and 7 3/4-degrees; at accelerated runs to 15 fps. landing tests were made without power and with half power, on models with depth of main step at centroid, 3.8 and 7% of the beam; gross loads 60.1 and 71.6 lbs.; C.G.'s at 24 and 34% MAC; at landing trim angles from 17-degrees to 4-degrees. Performance Characteristics of a Preformed Elliptical Parachute at Altitudes between 200,000 and 100,000 Thousand Feet. Obtained by In-Flight Photography 1963 Originally recorded in 16mm, Silent, Color, 3820ft., 34min. Performance of 26 Meter Diameter Ringsail Parachute in a Simulated Martian Environment 1967 16mm, Silent, Color, 80ft., 2.5min. Performance of a 16.6 Meter Diameter Cross Parachute in a Simulated Martian Environment 1968 Originally recorded in 16mm, Silent, Color, 112ft., 3min. Performance of a 16.6 Meter Diameter Modified Ringsail Parachute in a Simulated Martian Environment 1968 Originally recorded in 16mm, Silent, Color, 150ft., 4min. Performance of a 19.7 Meter Diameter Disk-Gap-Band Parachute in a Simulated Martian Environment 1968 Originally recorded in 16mm, Silent, Color, 150ft., 4min. Performance of a Towed, 48-Inch Diameter (121.92) Balluet Decelerator Tested in Free-Flight Mach Numbers from 4.2 to 0.4 1968 Originally recorded in 16mm, Silent, Color, 70ft., 2min. Performance of Long Range Hypervelocity Vehicles, Ames Aero Lab 1962 16mm, Sound, Black & White, 1100ft., 30min. Perspective Tunnel Display for 3-D Helicopter Approach and Landing 1978 16mm, silent, Color, 12.5min. PFT Transonic Conference Movie 16mm, Silent Photographic Study of Solid Propellant Burning in a Acceleration Environment 1969 16mm, Silent, Color, 1188ft., 33min. Pilot- Escape Tests in Free Spinning Tunnel 16mm, Silent, Black & White Pilotless Aircraft Research 16mm, Silent, Color Pilotless Aircraft Research 16mm, Sound, Color Pilotless Aircraft Research 16mm, Silent, Color Pitch-up and Directional Divergences as Demonstrated by Free-Flight Model Tests. 16mm, Silent, Black & White, 100ft., 4 min. Planetary Biology at Ames Research Center 16mm, Silent, Color Plastic Deformation of Aluminum 16mm Plate Post Box Beam Test Structure 16mm, Silent, Black & White Polaris 0.4-Scale Stability Model R34-3 1959 16mm, Silent, Color, 170ft., 5min. Polaris Nose Ablation Tests in Wallops Island pre-flight Jet 16mm Polaris PARD 1/3-Scale Reentry Body Flight Test 16mm, Silent, Black & White Polish Smoke Flow 16mm Presents air streamline flow around cylinders, airfoils and wings provided with slots, flaps, etc., at various angles of attack. Pollution (1) B-Wind S.Perf.master (2) 16mm Mag. Mix Track (3) 16mm Opt Track 16mm, Sound, Color, 120ft., 3min. Preflight Jet Structural Integrity Test of Model Cowling Used on the Free-Flight Afterbody Pressure Investigation Supporting the WS-107A Project by the Pilotless Aircraft Research Division of the NACA Langley Laboratory 1958 16mm, Silent, Black & White, 795ft., 22min Prelim. Data Conf. Film Tank. Mdl. 248 Dsn. # DR-56 16mm, Silent, Color The DR-56 is class VA flying boat having a normal gross load of 130,000 lbs. a planing-tail hull, sweptback wings with integral wing-tip floats, and wing-root jet power plant installation. Operational centers of gravity are located aft of the main step. The investigation was made of a 1/17-size jet-powered dynamic model and all data are presented in terms of full-size values. All take-offs and landings were made with elevators fixed. Taxying to hump was run at normal gross load in waves 8ft. high and 200 ft. long; take-offs at normal gross load were made in smooth water and in waves 8-ft. Height and 350 ft. long at an average acceleration of 4 ft./sec./sed.; and landings were made at normal gross load in smooth water and at 110,000 lbs. in waves 8ft. high and 300ft. long and 8ft. high and 350 ft. long at average deceleration of 1.5 ft./sec./sec. with and without freedom of fore and aft restraint. Prelim. Data Conf. Tnk. Mdl. 248 Dsn # DR-56 Part 3 16mm, Silent, Color Preliminary Data (B-29 Tank #2) 1953 16mm, Silent, Black & White Ditching tests were made in calm water in Tank #2 on a 1/20-scale model of the Army B-29 airplane with C.G. at 25% MAC and 3.2 in. above fuselage center line, weight of 105,000 lb., and scale strength flaps. Tests were run on the complete model, simulating no failure, on model with bomb-bay doors, and section between bomb-bay doors removed, simulating their failure; and on model with nose window, nose wheel door, main wheel doors, bomb-bay doors, section of fuselage between bomb-bay doors, camera hatch, main entrance door, and tail skid door removed, simulating their failure. The landing attitudes war 1-degree and 9-degrees, flap deflection 45-degree, and velocities 120 and 133 MPH. When the model was tested at 1-degree altitude, 3-wheel landing altitude, the flaps did not fail on about half of the ditchings and the model dived. When ditched with one wing low, the model made a violent turn. Preliminary Data B-29 Catapult Part 1 16mm, Silent, Black & White Preliminary Data- B-32 16mm, Silent, Black & White Ditching tests were made in calm water in Tank # 2 on 1/20 Scale undamaged model of the Army B-32 with C.G. at 29% MAC; weight represented 100,000 lbs; flaps at 40-degrees, 20-degrees, and 0-degrees; speeds of 115, 118, 132, and 140 MPH; attitudes 13-degrees, 6-degrees, and 0-degrees; decelerations from 1 g to 3.5 g; and runs from 4 to 11 lengths of fuselage. Preliminary Data Film B-32 Ditching Tank 2 (Part 2) 16mm, Silent, Black & White Ditching tests were made in calm water in Tank #2 on a 1/20 scale model of the Army B-32 airplane with damage simulated. The weight represented 100,000 lbs and the C. G. was located at 29.7% MAC and 26.2 in. above the center line of the fuselage. Tests were made with damage simulated by removal of the bomb-bay doors (fore & aft), radio and radar antennae, landing gear doors (nose & main) and a section of the lower fuselage extending back from the front of the bombardier's compartment to the rear of the nose wheel door. The attitude angles were o-degrees, 6-degrees, and 13-degrees; flap deflections 0-detrees, 20-degrees, and 40-degrees; speeds range from 101 to 140 MPH maximum decelerations ranged from 1.2 to 4 g; and lengths of run ranged from 2 to 7 times the fuselage length. Preliminary Data Film Illustrating the Tow Characteristics of a 0.097-Scale Model of the SV-5 Vehicle for Three Noses Tow Attachment Positions 1965 16mm, Silent, Color, 320ft., 9min. Preliminary Data Film Illustrating the Tow Characteristics of an 0.097-Scale Model of the SV-5 Vehicle 1965 16mm, Silent, Color, 675ft., 18.5min. Preliminary Data Film Illustrating the Tow Characteristics of Several Models of the SV-5 Vehicle 1965 16mm, Silent, Color, 745ft., 21min. Preliminary Data Film of a Transition Flight Test of 1/8-Scale Model of Hitler S-18 VTOL Airplane 1957 16mm, Silent, Color, 65ft., 2min. Preliminary Data Film of Flight Tests of 1/4-Scale Model of the Vertol VTOL Flying Test Bed 1957 16mm, Silent, Black & White, 52ft., 1.5min. Preliminary Data Film of Tuft Test of a 1/8-Scale Model of Hiller X-18 VTOL Airplane 1957 16mm, Silent, Black & White, 450ft., 12.5min. Preliminary Data Film on Inverted Spin Tests of a 1/28-Scale North American FJ-4 Model 1956 16mm, Silent, Black & White Preliminary Data Film on Rocket Recovery Spin Tests on a 1/25-Scale Lockheed F-104A Model 1957 16mm, Silent, Black & White, 280ft., 8min. Preliminary Data Film on Supplementary Free-Spinning Tests of a 1/28-Scale Model of the North American FJ-4 Airplane 1957 16mm, Silent, Black & White, 620ft., 17min. Preliminary Data Film on the 1/25-Scale Model of the Chance Vought XF8U-1 Airplane 16mm, Silent, Black & White, 285ft, 12min Preliminary Data Film on the 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane-- Part II 16mm, Silent, Black & White, 280ft, 9min Preliminary Data Film on the Chance-Vought XF8U-1 Airplane 16mm, Silent, Black & White, 580ft, 16min Preliminary Data Film on the Free-Spinning Tests of the 1/28-Scale Model of the North American FJ-4 Airplane 16mm, Silent, Black & White, 320ft, 18min Preliminary Data Film-Part 1 This film is the unedited copy of Part 1 of the preliminary data film showing tank ditching tests of the Army A-26 airplane. The edited copy of this film is listed under NACA Film No. 324-0. Preliminary Data Model 208 1946 16mm, Silent, Black & White Investigation was made in Tank #1 of spray and stability characteristics of a1/5.5-scale dynamic model of the Columbia XJL-1 amphibian. The full scale amphibian had a 6.33 ft. beam, hull 35.75 ft. long, 43.60 ft. overall length, 50 ft. wing span, 13,000 lb. maximum gross load, and load coefficient of 0.80. Bow spray during the beginning of take off run is shown for gross loads of 10,800 and 13,000 lb.; C.G. at 26% MAC; flaps deflected 30-degrees; and take-off power. Flap spray and flow under step during a take-off run are shown for a gross weight of 13,000 lb.; C.G. 35% MAC; flaps deflected 30-degrees; take-off power; and elevators deflected to -30-degrees. A constant speed run of 42 knots is shown in which the trim was gradually increased from 3-degrees to the upper limit of 12-degrees, through the region of intemediate porpoising -8-degrees to 10-degrees then gradually decreased to original value. Landings at one-quarter take-off power are shown for gross weights of 10,800 and 13,000 lb.; with flaps at 60-degrees; C.G. at 24% MAC; over a trim angle range from 13-degrees to 4-degrees. Preliminary Data Model 212-A Tank 1 1946 16mm, Silent, Black & White Landing tests were made in rough water in Tank #1 on the 1/7-size dynamically similar, powered model of the Grumman XJR2F-1 amphibian with a gross load which corresponds to 22,600 lb. full-scale, flaps deflected 45-degrees, C.G at 25% MAC, and carriage deceleration 3.0 ft./sec./ sec. Landings were made in waves 8 in. high by 15 and 20 ft. long at trim angles from 12-degrees to 5-degrees. Preliminary Data Model 212-B 16mm, Silent, Black & White Preliminary Data on the 1/25-scale Model Chance-Vought XF8U-1 Airplane 16mm, Silent, Black & White, 775ft, 32min Preliminary Data on the 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane 16mm, Silent, Black & White, 450ft, 18min Preliminary Date B-29 (Catapult Part I Calm and Rough Water) 16mm, Silent, Black & White Catapult tests were made using the seaway catapult at Langley Field, VA., on a 1/20-scale model of the Army B-29 airplane in calm and rough water. Scale strength flaps were used and all values; weight of 105,000 lbs. C.G. at 20% MAC and 3.2 in. above the fuselage Center line; attitude angles of 1-degree and 9-degree; flap deflections of 45-degree; and velocities of 104 and 128 MPH; refer to the full-scale airplane. Calm water tests were made with bomb-bay doors and section of fuselage between them removed to simulate their failure; and with nose window, nose wheel door, main wheel failure. Tests were also made with wave crests parallel to flight path and perpendicular to flight path. Preliminary Date Film: Landing Tests: XP4Y-1 Flying Boat 16mm, Silent, Black & White Preliminary Film Ditching Test in Tank #2 of Model P-38 1945 16mm, Silent, Black & White Ditching tests were made in calm water in Tank #2 with a 1/9-scale model of the Army P-38 airplane with scale strength flaps, weights of 14,900 lbs. and 16,000 lbs., C.G. at 27.7% MAC and 4.6 in. below thrust line. Test were made with no simulated damage; with three landing-wheel doors removed; and with hydroflaps of 19\8 in. length, 9 in. width and 30-degree angle with thrust line were installed on the model 97 in. aft of the nose. Attitudes were from 13-degrees to 2-degrees, flap settings were from 0-degrees to 37-degrees, and velocities ranged from 110 to 140 MPH. Preliminary Flight Tests of 1/7-Scale Radio-Controlled Model of the X-15 Airplane 1957 16mm, Silent, Color, 200ft., 5.5min. Preliminary Flight Tests of a 0.13-Scale Model of the Dornier DO-31 1962 16mm, Silent, Black & White, 285ft., 8min. Preliminary Flight Tests of a 1/6-Scale Model of the Hawker P.1127 1960 16mm, Silent, Black & White, 90ft., 2.5min Preliminary Flight Tests of a 1/6-Scale Model of the Hawker P-1127 1960 16mm, Silent, Black & White, 280ft., 8min. Preliminary Flight Tests of Flying Jeep Model 1958 16mm, Silent, Black & White, 24ft., 1min. Preliminary Flight Tests of Flying Jeep Model 1958 16mm, Silent, Black & White, 160ft., 4.5min. Preliminary Free-Flight Tests of a 1/6-Scale Model of the Bell D190B 1961 Originally recorded in 16mm, Silent, Black & White, 280ft., 7.5min. Preliminary Hovering Flight Check of 1/8-Scale Model of Hiller X-18 VTOL Airplane 1957 16mm, Silent, Black & White, 107ft., 3min. Preliminary Hydrodynamic Investigation of a 1/17-Scale Model of a Mach 3 Water Based Aircraft 1958 16mm, Silent, Black & White, 950ft., 54min. Preliminary Investigation of a Paraglider 1959 16mm, Silent, Black & White, 285ft., 8min. 19980227770 A preliminary investigation of the aerodynamic and control characteristics of a flexible glider similar to a parachute in construction has been made at the Langley Research Center to evaluate its capabilities as a reentry glider. Preliminary weight estimates of the proposed vehicle indicate that such a structure can be made with extremely low wing loading. Maximum temperatures during the reentry maneuver might be held as low as about 1,500 F. The results of wind-tunnel and free-glide tests show that the glider when constructed of nonporous material performed extremely well at subsonic speeds and could be flown at angles of attack from about 200 to 900. At supersonic speeds the wing showed none of the unfavorable tendencies exhibited by conventional parachutes at these speeds, such as squidding and breathing. Several methods of packing and deploying the glider have been successfully demonstrated. The results of this study indicate that this flexible-lifting-surface concept may provide a lightweight controllable paraglider for manned space vehicles. Preliminary Investigation of a Technique to Determine Whether the Mercury Capsule is Stable During the Transonic Phase of Reentry. 1959 16mm, Silent, Black & White, 530ft., 15min. Preliminary Landing Tests of a 1/6-Scale Dynamic Model of a Lunar Excursion Vehicle 1962 Originally recorded in 16mm, Silent, Black & White, 240ft., 6.5min. Preliminary Materials Tests in a Chemical Jet 1956 16mm, Silent, Color, 200ft., 5.5min., Preliminary Materials Tests in a Chemical Jet 1956 16mm, Silent, Color, 280ft., 3min. Preliminary Spin Tests of a 1/30-Scale Model of the North American X-15 Airplane in the Langley 20-Foot Free-Spinning Tunnel 1957 16mm, Silent, Black & White, 220ft., 6min. Preliminary Studies of the Erosion of Fine Particles Resulting From Jet Impingement in a Vacuum 1964 16mm, Silent, Black & White, 520ft., 14.5min. Preliminary Study of the Subsonic Dynamic Stability of All-Wing Airplane Configuration Flying at 90-Degree Angle of Attack 1959 16mm, Silent, Black & White, 720ft., 20min. Preliminary Tests of a Flexible Rotor System Conducted at the Langley Research Center 1961 Originally recorded in 16mm, Silent, Black & White, 664ft., 18min. Preliminary Tests of an 0.034-Scale Model of the Chance-Vought F7U-3 Airplane on the Spin Tunnel Catapult Facility 16mm, Silent, Black & White, 200ft, 5min Preliminary Tethered Hovering Tests of the Doak VZ-4DA, Chrysler VZ-6C, and Short SC-1 1960 16mm, Silent, Black & White, 341ft., 9.5min. Preliminary Transition Flight of 1/8-Scale Model of Hiller X-18 VTOL Airplane 1957 16mm, Silent, Black & White Preliminary Wind-Tunnel Investigation of Pilot Escape by Nose Jettisoning--May 1948 1948 16mm, Silent, Black & White Preparation and Flight Test of the 0.133-Scale Rocket-Powered Model of the Convair XFY-1 Airplane 16mm, Silent, Color, 165ft., 4.5min. Preserving the Earth's Atmosphere (1974 Inspection Film Series) 1975 16mm, Sound, Color, 665ft., 18.5min. Preserving the Earth's Atmosphere 1961 16mm, Sound, Color Progress Report on Tests of NACA Hydro-Skis for High Speed Airplane 1947 16mm Project 1226.--No. 1, Configuration 1 1956 16mm, Silent, Black & White, 5min. Project Fire Heat Shield Ejection Tests 1963 16mm, Silent, Color, 218ft., 6min. Project fire Heat Shield Ejection Tests-Langley 9-by-6-Foot Thermal Structures Tunnel (All Camera Speeds are Approximate) 1962 16mm, Silent, Black & White, 485ft., 14min. Project Mercury Congressional Film Report No. 1 1962 16mm, Sound, Color, 1200ft., 33min. Project S-55 1962 16mm, Sound, Color, 982ft., 27min. Project Shotput 1960 16mm, Silent, Color, 130ft., 3.5min. Project Tom-Tom, Part 2 16mm, Silent, Black & White Project Tom-Tom-Langley 19 inch Pressure Tunnel Part 1 16mm, Silent, Black & White, 450ft., 19min. Propeller Whirl Demonstration 1961 16mm, Silent, Black & White Protecting our Marine Environment (1974 Inspection Film) 1975 16mm, Sound, Color, 688ft., 19min. Pyrolytic Graphite-Coated AGX Graphite Leading-Edge Tests in the 1500-kw Subsonic Arc-Jet Facility at the Langley Research Center 1960 16mm, Silent, Color, 195ft., 5.5min. Pyrrone and Other Organic Ablation Materials 1960 16mm, Silent, Color, 115ft., 3min. Qualifications Tests of the Aeroproducts Wind-Driven Auxiliary Hydraulic Power Source 16mm, Silent, Black & White, 210ft., 6min. Quieter Airport Communities (Acoustics and Noise Reduction Division) 1975 16mm, Sound, Color, 708ft., 20min. Radar Tracking Evaluation Flight 19. F3D Equipped with APQ-35B Radar Tracking an F-51 Airplane (Altitude 25,000', Airspeed 330 mph) 16mm, Silent, Color Radiant Heating Test Multiweb Wing Section 1957 16mm, Silent, Black & White, 100ft., 3min. Ranger VII Photographers of the Moon 16mm, Silent, Black & White, 7min. Rayn Saturn-Booster Recovery Configuration 1961 Originally recorded in 16mm, Silent, Black & White, 310ft., 8.5min. Raytheon Structural Integrity Test of Raytheon Developed Ablating Material for Application to the Super Hawk Anti-IRBM Missile 1959 16mm, Silent, Color, 325ft., 9min. Reactions of Materials in Hi-Temperature Air Flows 1957 16mm, Silent, Color, 440ft., 12min. Reduced Gravity Simulator for Study of Man's Self Locomotion 16mm, Sound, Color, 10min. Reentry Body Stability Tests Conducted in Langley Spin Tunnel 1958 Originally recorded in 16mm, Silent, Black & White, 40ft., 1min. Rendezvous Docking Simulator 1963 Originally recorded in 16mm, Color, 180ft., 5min. Republic MX-1554-A Capsule Tests-- Preflight Jets at Wallops Island, VA (M-1.59; Reels I, II,III, and IV) 16mm, Silent, Black & White Republic XF-12 Stall Studies 1945 16mm, Silent, Black & White Stall studies were made by means of tufts in the 19 ft. pressure tunnel on the 1/8.33-scale model of the Republic X-F-12 to ascertain the stall progression of the complete model with the original Republic wing duct inlets. The tests were made with propellers operating; all control surfaces neutral; at an RN of approximately 2,380, 000; with flaps retracted and deflected at 65-degrees; thrust coefficient of 0; with 0.50 and 0.75 rate power; over an angle of attack rang from 0.1-degrees to 21.2-degrees; and a lift coefficient range from 0.01 to 3.16. View of the left and right wings, the fuselage, the engine nacelles, and tail surfaces are shown for angle of attack, increasing from 6.4-degrees to 21.2-degrees. Republic XF-12 Stall Studies 16mm, Silent, Black & White Republic XP-84 7x10 Tunnel 16mm, Silent, Black & White Research on Airplane Spins 16mm, Silent, Color, 513ft. Research on Airplane Spins 16mm, Sound, Color Response of Simple Panels to Intense Noise (Panel Width: 11in., Panel Length: 13in., Frequency, 135 CPs, 1957 16mm, Silent, Black & White, 150ft., 4min. Results of a Free-Flight Test to Determine the Performance Characteristics of a Towed, Conical Decelerator 1969 16mm, Silent, Color, 90ft., 2.5min. Results of Intravehicular Manned Cargo-Transfer Studies in Simulated Weightlessness 1972 16mm, Silent, Color Results of This Series are Published in NASA-SP-298 in the Article Entitled Zero 'G' Manual Cargo-Transfer Originally recorded in 16mm, Silent, Black & White Rhode Film- Parts 1 and 2 16mm Richard Whitecomb-- The Story Behind a Great Discovery 16mm Rocket Launch and Track of Fire Tail 16mm, Silent, Color Rocket Model Flight Tests-- B-58 Program 16mm, Silent, Color, 430ft, 18min Rocket Motor Ignition by Impact (Photographs Taken with a Camera Capable of Framing Rates of 1,500,000 Per Second) 1959 16mm, Silent, Black & White, 55ft., 1.5min. Rocket Scenes 16mm, Silent, Color Rocket Trajectory 16mm, Silent, Black & White Roof-Top Stol-Port Flow Visualization 1971 16mms, Sound, Color, 23min. Rotary Balance Tests of a 1/40-Scale of the Convair B-58 Airplane in the Langley Transonic Dynamics Tunnel 1960 16mm, Silent, Black & White, 270ft., 7.5min, Rotor Blade Flutter of the NACA Dynamic Model of the XH-17 Two-Blade Jet-Driven Helicopter 16mm, Silent, Black & White, 100ft., 4min. ROUGH RIDERS II (PRINT) 1961 16mm, Color Rough Water Behavior of Tilt-Wing Configuration With Hydrofoil Gear 1958 16mm, Silent, Color, 325ft., 9min. Rough Water Landing Investigation of 1/14-Scale Model of the Panto Base C-123 Airplane with Shock Absorbers--Part IV 16mm, Silent, Black & White Rough Water Landing Investigation Panto Base Version C-123 Airplane-Part III 16mm, Silent, Black & White, 100ft., 22min. Rough Water of Vosper Design P.T. Boat Model (Part II) 1949 16mm, Silent, Black & White Tests were made, in the Langley Tank #1, of the Vosper design P.T. boat model, in smooth water with spray strips; in uniform waves of height 3.5 in. and length 24 ft.; and waves of length 17 ft. and height for 4.5 in.; at velocities of 15, 23, and 30 ft./sec. Rough Water Taxi Wing Root Configuration (model 322) 16mm Rough Water Taxiing Characteristics of a 1/13.33-Scale Jet-Powered Dynamic model of the Martin XP6M-1 Flying Boat 16mm, Silent, Black & White Rough Waters of Plum Design P.T. Boat Model (Tank 1) 1949 16mm, Silent, Black & White Preliminary runs were made with the model, with spray strips installed, the smooth water and in uniform waves 3.5 in. high and 24 ft. long, and 4.5 in. high and 17 ft. long, at velocities from 15-37 ft./sec. S-3 Energetic Particle Satellite Operational Despin Tests 1961 16mm, Silent, Black & White, 2325ft., 1hr. 6min. S-3 Paddle Erection Tests 1961 16mm, Silent, Black & White, 1850ft., 50min. Safer Flying Plane 1947 16mm, Silent, Black & White San Marco Documentary and Launch Track of S-137R 16mm, Silent, Color, San Marco 16mm, Silent, Black & White Saturn--A Giant Thrust into Space Originally recorded in 16mm, Color, Sound, 369ft., 10.5min. SB-20 Flutter 16' W.T. 16mm SB2CU Flutter 16mm SB2U Flutter 1943 16mm Presents tests run in the 16-foot high-speed tunnel on the SB2U-2 airplane to determine the flutter speed, the frequency at which flutter occurs, and the behavior of the airplane at speeds below the flutter speed., The flutter which was found to have a frequency between those of torsion and bending, occurred at 16 cycles per second and flutter speed was 20% higher than the 125 MPH predicted speed. The vibration testing equipment, which has amplifiers, bridges and oscillograph recording equipment, used for the test was built by the Glenn L. Martin Co. There appeared in the oscillograph record a high frequency type of skin flutter which evidently delayed the flutter by increase in the internal damping. SB2U Flutter 16mm, Silent, Black & White SB2U Flutter 1939 16mm, Silent, Black & White SB2U Flutter Film 16mm, Silent, Black & White Scale Model of Submarine Albacore in Langley Full-Scale Tunnel 16mm, Silent, Black & White Scaled Lunar Module Jet Erosion Experiments 1966 Originally recorded in 16mm, Silent, Color, 185ft., 5.1min. Scar Structural Panel Program Rohrbond Panel 1-13-75 1975 16mm, Sound, Color, 600ft. Schileren 8' HST 1951 16mm Schileren Movies of the 8-Inch Diameter Rigid Parachute Model of Cook Research Laboratories Taken During the Third Phase of Testing in the Langley Unitary Plan Wind Tunnel 1958 16mm, Silent, Black & White, 870ft., 24min. Schileren No. 1 16mm Presents Schlieren photographs of flow over symmetrical airfoils of various thicknesses, namely: NACA 0040-65; 0015-45; 0025-45, 0040-45; 0040-64; and 0040-63. The purpose of the study is to indicate flow changes which result from variations in maximum thickness, maximum thickness location, and Mach numbers. Test Mach numbers ranged from 0.000 to 0.810. Schlieren Motion Pictures of a Cascade of 65(4A10)06 Blade Sections in Reverse (Trailing Edge Forward) 1956 16mm, Silent, Black & White, 140ft., 6min. Schlieren Movies of Flexible Parachute Models of Cook Research Laboratories Taken Turing the Fifth Phase of Testing in the Langley Unitary Plan Wind Tunnel 1959 16mm, Silent, Black & White, 2100ft., 59min. Schlieren Movies of the 8-Inch Diameter Rigid Parachute Model of Cook Research Laboratories Taken During the Second Phase of Testing in the Langley Unitary Plan Wind Tunnel 1958 16mm, Silent, Black & White, 331ft., 6.5min. Schlieren Movies of the 8-Inch Diameter Rigid Parachute Model of Cook Research Laboratories, Taken in the Langley Unitary Plan Wind Tunnel 1958 16mm, Silent, Black & White, 555ft., 15min. Schlieren Movies of the 8-Inch Diameter Rigid Parachute Model of the Cook Research Laboratory Taken During the Fourth Phase of Testing in the Langley in the Langley Unitary Plan Wind Tunnel 1958 Originally recorded in 16mm, Silent, Black & White, 845ft., 23min. Schlieren Part 2 16mm, Silent, Black & White Pressure distribution diagrams are given for NACA 16-025 at angles of attack of 0-degrees and 6-degrees for Mach nos. from 0.332 to 0.789. Variation of normal-force coefficient with Mach no. for the NACA 16-025 airfoil is given for angles of attach from -2-degrees to 12-degrees. The effect of Mach no. on the slope of the lift curve is given for angles of attack from -2degrees to 12-degrees and Mach no. from 0.355 to 0.75. Pressure distribution diagrams are given for NACA 16-040 at angles of attack of 0-degrees and 6-degrees for Mach nos. from 0.325 to 0.729. Variation of normal-force coefficient with Mach no. for the NACA 16-040 airfoil is given for angles of attack from -2degrees to 12-degrees and Mach no. from 0.325 to 0.735. The effect of Mach no. on the slope of the lift curve is given for angles of attack from -2-degrees to 12-degrees and mach nos. from 0.33 to 0.70. Schlieren Photos of Flow Over NACA 65A012 Airfoil (a=0-Degrees to 8-Degrees. M=0.7 to 1.0) 16mm, Silent, Black & White, 200ft., 8min. Schlieren Runs of 1/20-Scale Model of the X-15 in Langley Unitary Wind Tunnel 1959 16mm, Silent, Black & White, 1200ft., 33min. Schlieren Studies of Transonic Buffet of Nose Cone 1960 16mm, Silent, Black & White, 308ft., 8.5min. Scout 1 Alpha F62-3094 16mm, Silent, Black & White Scout 110, L5-985, O-EKTA, Assy. Documentary 16mm, Silent, Black & White Scout 114 L5-946 NASA Wallops Station Wallops Island, Va. 16mm, Silent, Color Scout 122 Tech Film 16mm, Silent, Color Scout A-405: ""G"" Tests 16mm, Silent, Black & White Scout Cold Separation Clamp Malfunction Tests 1962 16mm, Silent, Black & White, 535ft., 15min. Scout Launch Vehicle Progress Report 1972 16mm, Sound, Color, 1111ft., 31min. Scout Launch Vehicle Progress Report, May 1975 through Oct. 1976 1976 16mm, Sound, Color, 34min. Scout Launch Vehicle Progress Report, Nov. 1, 1976 - Oct. 31, 1979 1979 16mm, Sound, Color, 31min. Scout Progress Report 1973 1974 16mm, Sound, Color, 32min. Scout Progress Report (Nov. 1973-Apr 1975.) 1975 16mm, 1200ft., 30min. Scout Project Group: CVC Tests Separation 16mm, Silent, Black & White Scout S-177C Solard 10 16mm Scout ST-1 Payload Details Scout Test Vehicle 1960 16mm, Sound, Color 480ft., 13min. Second Progress Report on Tests of NACA Hydro-Skis for High Speed Airplanes, Model 229, Part 2 1947 16mm, Silent, Color Self Locomotion in Earth and Lunar Gravity 1966 16mm, Silent, Color, 100ft., 3min. Separation Studies of a 1/40-Scale Dynamically Similar TCP Fuel Tank from the B-58A Airplane Conducted at the NASA Wallops Statuons Preflight Jet--Phase 2 16mm, Silent, Black & White, 940ft., 26min. Shaped Charge Separation Tests in the 60- Foot Vacuum Sphere 1962 16mm, Silent, Black & White, 720ft., 20min. Shimmy W-1 16mm Shot Put No. 1 1959 16mm, Silent, Black & White, 275ft., 8min. Shot Put No. 2 1960 16mm, Silent, Color, Black & White, 330ft., 9min. Shot Put No. 3 1960 16mm, Silent, Black & White, 446ft., 12.5min. Shot Put No. 4 1960 16mm., Silent, Black & White, 482ft., 13.5min. Shot Put. no. 5 1960 16mm, Silent, Black & White, 273ft., 7.5min Shuttle Flight Tests 16mm, Silent, Color Simulated Flight Investigation of Sealed-Speed Elastic Swept-Wing Bomber and Fighter Models Coupled Wing-Tip to Wing-Tip 16mm, Silent, Black & White, 440ft, 18min Simulated Nike Asp Separation Tests Conducted at the Hypersonic Physics Test Area, Langley Field 1961 16mm, Silent, Black & White, 235ft., 6.5min. Simulation and Flight Test of a Simple Homing Missile 16mm, Silent, Black & White, 200ft, 5.5min Simulation on the Analog Computer 1964 16mm, Sound, Color, 262ft., 7.5min. Simulation Study of a High Performance Aircraft Including the Effect on Pilot Control of Large Acceleration During Exit and Reentry Flight 1958 16mm, Silent, Black & White, 7.5min. Simulator 16mm, Silent, Black & White Simulator on the Analog Computer 16mm, Silent, Color Simulator Study of Lunar Orbit Establishment 1965 16mm, Silent, Black & White, 250ft., 10.5min. Simulators: Static Rendezvous Chair, Three Axis, Gemini 16mm, Silent, Color, 20min. Six Stage Reentry Physics Research Vehicle 1959 16mm, Silent, Color, 620ft., 17min. Small Scale Investigation of the Operational Dust-and-Debris Problems of Helicopters and Other VTOL Aircraft for a Range of Downwash Velocities and Types of Terrain 1958 16mm, Silent, Color, 130ft., 3.5min. Smoke Drag #2 16mm, Silent, Black & White Smoke Drag 16mm Smoke Drag 16mm, Silent, Black & White Smoke Flow in Flight 16mm Smoke in Flight Smoke flow studies over wings and tail surfaces of an airplane in flight are show. 16mm Smoke in Flight 16mm Smoke Launching H202 Tests ST-1 Assembly 16mm, Silent, Color Smoke Lift 16mm, Silent, Black & White Smoke Lift 16mm, Silent, Black & White Smoke Lifts 16mm, Black & White A study of streamline flow, by means of smoke, around a flat plane, a plain airfoil and an airfoil incorporating high lift devices. Lift and drag brought about by various configurations and changes in angle of attack are studied. Smoke Over Suction Wing PRT 16mm Smoke Trail Wind Shear Measurements 1965 16mm, Sound, Color, 342ft., 9.5min. Smooth Water Take-Offs and Landings of Langley Tank Model 389 (N. P. Princess Flying Boat) 1959 16mm, Silent, Color, 175ft., 5min. Solid Propellant Rocket Fuel Impacted by 0.22-Inch Steel Sphere 1959 16mm, Silent, Black & White, 30ft., 1min. Some Aspects of Aerodynamics of STOL Ports 1971 16mm, Silent, Color, 130ft., 3.5min. Some Effects of Vanes and of Turbulence in Two Dimensional Wide Angle Subsonic Diffusers 1958 16mm, Silent, Black & White, 280ft., 8min. Tests on two aspects of the behavior of wide-angle, plane-walled, two-dimensional diffusers with essentially incompressible flow have been conducted in the Mechanical Engineering Laboratory at Stanford University. First, a thorough study of the flow mechanism has been made using dye injection in a water table. The four regimes of flow found are delineated on graphs in terms of the three important parameters. Test data from a large water-table unit and a small water-table unit are given. Second, data are presented which demonstrate means for producing efficient diffusers for total included angles up to at least 45? by use of simple, short, flat vanes. Some Examples of the Use of Wind Tunnels for the Investigation of Flutter 1958 16mm, Silent, Color, 8.5min. Some Examples of Transonic Flows Over Various Payload-Booster Configuration 1961 16mm, Silent, Black & White Some Experiments with Insulated Structures 1957 16mm, Silent, Color, 3.5min Some Preliminary Notes on a Parachute Recovery System for Transport Airplanes 1960 16mm, Black/white, silent Some Spin-Recovery Parachute Tests of the 1/25-Scale Model for the Lockheed F-104A Airplane in the 20-Foot Free-Spinning Tunnel 1958 16mm, Silent, Black & White, 300ft., 12min. Some Studies of Liquid Rotation and Vortexing in Rocket Propellant Tanks 1962 16mm, Silent, Black & White, 700ft., 20min. Soundless Airplane 16mm Space and Technology 16mm, Silent, Black & White, 2min. Space Control Systems 1959 16mm, Silent, Black & White, 380ft., 10.5min. Space Electronics Technology- LeRC 16mm, Silent, Color, 21min. Space in the Age of Aquarius 1972 16mm, Sound, Color, Space Lab 16mm, Silent, Color Space Research 1959 16mm, Sound, Color, 980ft., 27min. Space Shuttle Heat Shield Refurbishment 1972 16mm, Silent, Color 1065ft., 30min. Space Shuttle: Overview 1980 16mm, Sound, Color Space Station Research 1965 16mm, Sound, Color 140ft., 4min. Spacecraft Stabilization and Control 1968 16mm, Sound, Color, 700ft., 19.5min Spectral Measurements of Gas-Cap Radiation During Project Fire Flight Experiments at Reentry Velocities Near 11.4 Kilometers Per Second 1967 16mm, Silent, Black & White Spin & Recovery Characteristics of Three McDonnell Models- XF2H-1, F2H-1, and F2H-3 16mm Spin & Recovery characteristics of Tree McDonnell Model XF2H-1, F2H-1, F2H-3 16mm Spin and Recovery Characteristics of a Typical Spin-Tunnel Model and Operation of a Spin Simulator 1959 16mm, Silent, Black & White, 180ft., 5min. Spin and Recovery Tests of a 1/17-Scale Model of the Cessna T-37 Airplane 1957 16mm, Silent, Black & White, 2075ft., 24min. Spin and Recovery Tests of a 1/20-Scale Model of Grumman YAO-1 Airplane 1960 16mm, Silent, Black & White, 650ft., 18min. Spin and Recovery Tests of a 1/28-Scale Model of the Grumman A2F-1 Airplane 1962 16mm, Silent, Black & White, 550ft., 15.5min. Spin and Recovery Tests of a 1/28-Scale Model of the Grumman A2F-1 Airplane 1990 16mm, Silent, Black & White, 15min, 540ft. Spin and Recovery Tests of a1/20-Scale Model of the Grumman YAO-1 Airplane 1960 16mm, Silent, Black & White, 288ft., 8min. Spin and Recovery Tests on a 1/30-Scale Model of the North American A3J-1 Airplane 1960 16mm, Silent, Black & White, 475ft., 13min. Spin and Recovery Tests on a 1/30-Scale Model of the North American A3J-1 Airplane 1958 16mm, Silent, Black & White Spin and Recovery Tests on a 1/30-Scale Model of the North American A3J-1 Airplane 1958 16mm, Silent, Black & White Spin Clippings 16mm Spin Entry Tests of a 1/40-Scale Model of the Convair B-58 Airplane 1961 16mm, Silent, Black & White, 5548ft., 2hr. 40min. Spin Entry Tests of a 1/60 Scale Model of the North American B-70 Airplane 16mm, Silent, Black & White Spin Recovery Parachute Tests of the 1/25-Scale Model of the Lockheed F-104B Airplane in the 20-Foot Free-Spinning Tunnel 1957 16mm, Silent, Black & White, 100ft., 3min. Spin Test on the 1/40-Scale Model of the Convair B-58 Airplane 1960 16mm, Silent, Black & White,1060ft., 29min. SPIN TESTS (1948) 1948 16mm, Black & White Spin Tests Film on the 1/25-Scale Lockheed F-104B Model 1957 16mm, Silent, Black & White, 250ft., 7min. Spin Tests in RAE Vertical Wind Tunnel 16mm Preliminary tests of a miniature tunnel were made. Spinning tests were carried out in a large vertical tunnel of the RAE which is a 30ft. high and 12ft. in diameter. The models used are made of balsa wood,1/15th to 1/25th full scale. Models are kept in jigs to prevent distortion. They are made accurately to scale, care being taken to obtain correct balance and mass distribution. Method of balancing the models was shown. The moments of inertia are obtained from swinging tests carried out in hydrogen to eliminate effects of the relatively dense air. Spins shown at 1/4th of their actual speed. A dangerous flat spin was made and then the same model with raised tail was used. This insures a steeper spin from which recovery is easy. The use of a dashpot to change control positions during a spin was shown. Spin Tests of a 1/40-Scale Model of the Convair B-58 Airplane. Included are Erect and Inverted Spin Tests and Parachute Tests 1961 16mm, Silent, Black & White, 5000ft., 1hr. 17min. Spin Tests of a Radio-Controlled 13-Percent Scale Dynamic Model of the McDonnell F4H-1 Airplane 1959 16mm, Silent, Black & White, 290ft., 8min. Spin Tunnel Investigation Film of a 0.034-Scale Model of the Chance-Vought F7U-3 16mm, Silent, Black & White Spin Tunnel Investigation Film of a 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane 16mm, Silent, Black & White Spin Tunnel Investigation Film of a 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane 16mm, Silent, Black & White, 260ft, 6.5min Spin Tunnel Investigation of the Spin and Spin Recovery Characteristics of a 1/20-Scale Model of the Douglas XF4D-1 Airplane 16mm, Silent, Black & White Spin Tunnel Test Film of a 1/20-Scale Model of the North American T2J-1 Airplane 1959 16mm, Silent, Black & White, 840ft., 23min. Spin Tunnel Tests of a Cargo-Dropping Device 16mm, Silent, Black & White Spin Tunnel Tests of a Cargo-Dropping Device 16mm, Silent, Black & White Spin Tunnel Tests of a Flare-Stabilized Bluff Body 1958 16mm, Silent, Black & White Spin Tunnel Tests of Cargo-Dropping Device 16mm, Silent, Black & White Spinning and Parachute Tests of a 1/24-Scale Model of the Grumman F11F-Airplane 1957 16mm, Silent, Black & White, 750ft., 21min. Spinning and Tumbling Tests of a 1/18-Scale Model of the Ryan X-13 Airplane and Drop Tests of a 1/18-Scale Model of the McDonnell F4H-1 Airplane 1957 16mm, Silent, Black & White, 800ft., 35min. Spinning Tests of a 1/19-Scale Model of a North American T-28C Airplane 1959 16mm, Silent, Black and White, 700ft., 29min. Spinning, Recovery and Parachute Tests of a1/30-Scale Model of the McDonnell F4H-1 Airplane 16mm, Silent, Black & White, 425ft. Spray Characteristics of Model 203 1945 16mm, Silent, Black & White Spray characteristics tests were made in Tank #1 on a 1/10-scale powered dynamic model with a hull having a length-beam ration of 9.0 (NACA model 203). The model is the first of a series to investigate the effect of high length-beam ration on the stability and spray of multi-engined flying-boats. The wing, tail surfaces, power plant, depth of hull, basic deadrise and angle of afterbody keel are the same as for the Navy XPBB-1 seaplane. The test conditions and spray patterns shown correspond directly to a full-scale XPBB-1 with the hull length-beam ration increased and a reduction of hull frontal area of 23%, a reduction in volume of 10%, and a reduction of hull surface are of 4%. Take-off runs with full power were made at 1 ft/sec [2nd power] acceleration, with flaps down 20-degrees, elevators up 10-degrees for gross loads of 62,000 and 92,000 lbs. Spray striking wing and tail with propellers windmilling as high and severe at a gross load of 62,000 lb. The spray without power tends to impair seaworthiness during landings only. It follows that when hull dimensions are determined by spray characteristics alone, high length-beam ration offers a means of reducing hull frontal area and volume. Spray Tests Modified JRM-1 NACA Model 180 1944 16mm, Black & White, Silent Spray tests were made in Tank #1 on a 1/12 scale model of the JRM-1 flying boat (NACA model180), modified for a gross load of 165,000 lb., to determine the effect of gross load coefficient on bow spray during accelerated runs from 5-20 fps, at an approximate acceleration of 3/4 ft. per sec. per sec., covering a gross load coefficient range from 0.5 to 1.1. SST Wing Stair Escape System 16mm, Sound, Color, 440ft., 12.25min. ST-1 Firing and Copy of C.V. Doc 16mm, Silent, Black & White ST-3 Tracking 16mm, Silent, Color Stability Analysis and Trend Study of a Balloon Tethered in a Wind with Experimental Comparisons 1973 16mm, Silent, Black & White, 9min. Stability and Control Characteristics of a Model of an Aerial Vehicle Supported by Four Ducted Fans 1961 16mm, Silent, Black &White, 470ft., 13min. Stability and Control Flight Tests of a Vertically Rising Airplane Model Similar to the Lockheed XFV-1 Airplane 16mm, Silent, Color Stability and Control Flight Tests; Convair Vultee XFY-1; Transition Condition 16mm, Silent, Color, 510ft Stability and Control Tests of XF7U-1 Film records of Flight Tests of 1/10 Scale Model of Chance Vought XFTU-1 Airplane in the Langley FFT 16mm, Black & White, Silent Stability and Controlled Flight Tests of a Vertically Rising Airplane Research Model with Interchangeable Swept or Unswept Wings and X or + Tails 1956 16mm, Silent, Color Stage Separation Tests of the Martin W3-107A-2 (Titan) in the Langley Unitary Plan Wind Tunnel 1958 16mm, Silent, Color, 880ft., 24.5min. Stall Studies of a 1/4-Scale Model F-105 with Supersonic-Type Elliptical Inlet 16mm, Silent, Black & White Stall Studies of XB-35 19'P.T. 16mm, Silent, Black & White Stall studies were made, by means of tufts, in the 19 ft. pressure tunnel on a 1.7-scale semispan model of the XB-35 airplane, to observe the effects of the landing flap, the pitch-control flap and the leading-edge slot on the stalling characteristics of the model. The model was tested in conjunction with a reflection plane approximately 3/32 in. from the model. The tests were made at a Reynolds Number of 7,000,000, Based on MAC=44.98 in.; Mach number - 0.12; with landing flaps at 0-degrees and 43.3-degrees; pitch-control flaps at 0-degrres, -34.1-degrees; -14.-degrees; leading-edge slot open and closed; over a range of angles of attack from 0.1-degrees to 21-degrees; and lift coefficient range from -0.13 to 1.35. Flow over wing tip, center, and inboard areas as angle of attack increased to stall was shown. Stall Studies P-67 (Runs 1306, 1307, 1310, 1316) 1947 16mm, Silent, Black & White Stall studies were made, by means of tufts, on the P-67 airplane with propellers off, in the propeller research tunnel, at a tunnel velocity of 85 MPH. Tests were made with flaps and deflected 45-degrees; landing gear up and extended; Q/AV at high speed angle of attack, .60 and .67 outboard duct, .48 and .59 inboard duct; over an angle of attack range from -2-degrees to 18-degrees; and with cooling-air exits closed; and aileron angles of 0-degrees and -10-degrees. Stall Studies P-67 1947 16mm, Silent, Black & White Stall Studies P-67 1947 16mm, Silent, Black & White Stall Studies P-67 1947 16mm, Silent, Black & White Stall Studies XP-51 16mm, Silent, Black & White Stalling and Tumbling of a Radio Controlled Parawing Airplane Model 1964 16mm, Silent, Color, 170ft., 4.5min Stalling and Tumbling Tests of a Free-Flying Radio-Controlled 1/5.6-Scale Model of the Ryan Parawing Airplane 1960 16mm, Silent, Color, 90ft., 2.5min. Starting of M=3.0 Nozzle Exhausting to Atmosphere 1958 16mm, Silent, Black & White, 175ft., 5min. Static Tests of 5-Inch Diameter Spherical Rocket 1960 16mm, Silent, Color, 60ft., 1.5min Static Tests of a Step-Exhaust Model to Determine Jet Noise Attenuation due to Water 1956 16mm, Silent, Color, Still Shot of an Apparatus 16mm, Silent, Black & White Structural Dynamics Research- Titan III Launch Vehicle and Payloads 1966 16mm, Sound, Color, 520ft., 14.5min. Structural Fatigue and Air Safety (Australia) 16mm Structural Feedback Demonstration 1960 16mm, Silent, Color, 73ft., 2min. Structural Integrity Tests of University of Maryland Oriole Sounding Rocket 1959 16mm, Silent, Color, 5.5min. Structures Research Division Heating Tests on Mercury Shingle Specimens 1960 16mm, Silent, Color, 220ft., 6min. STS-1 Prime Crew Presentation Clip 16mm, Silent, Color Studies of Accelerations in Manned Vehicles During Exit and Reentry Flight 1959 Originally recorded in 16mm, Silent, Color, Black & White, 340ft, 9.5min. Studies of Flow Formation in a Small Hypersonic Arc Tunnel With Varying Model Size 1962 16mm, silent, Color, 75ft., 2min. Studies of Main Chain Aromatic Polymers 1963 16mm, Silent, Color, 225ft., 6min. Studies of the Unsteady Flows Past Airfoils in Langley 4""x19"" Wind Tunnel 16mm, Silent, Black & White Study of Airflow by Means of Smoke 16mm, Silent, Black & White Study of Several Factors Affecting Crew Escape Trajectories from the Space Shuttle Orbiter at Low Subsonic Speeds 1985 16mm, Silent, Color, 800ft., 22min. Study of the Effects of a Rocket Exhaust on Radio Frequency Signal Attenuation by the Use of a Recoverable Camera on the NASA Scout Vehicle 1563 16mm, Silent, Black & White, 155ft., 4min. Study of the Surface Flow on a 1/50-Scale Model of the X-15 at M=6.8 1960 16mm, Silent, Black & White, 383ft., 10.5min. Subsonic Flight Tests of a 1/7-Scale Radio-Controlled Model of North America X-15 Airplane with Particular Reference to High Angle-of-Attack Conditions 1960 16mm, Silent color, 420ft., 11.5min. Summary of Attached Inflatable Decelerator (AID) Development 1968 Originally recorded in 16mm, Silent, Color, 226ft., 6min. Summary of Past and Present Individual Lift Devices 1961 Originally recorded in 16mm, Silent, Color, 450ft., 12.5min. Summary Results- Ditching Investigations of Five Transport Films (Training Film 19) 16mm, Silent, Black & White The NACA is investigating, with models, the ditching characteristics of a series of transport airplanes, including the Lockheed Constellation (with and without Speed Pack attached), Lockheed Constitution, Douglas DC-4 and DC-6, and Boeing Stratocruiser, in calm water. Scale dynamic models with scale strength bottoms, made of balsa wood or cardboard bulkheads and balsa stringers and covered with waterproof paper or aluminum sheet, are launched so that they glide freely onto the water. The scale strength bottom sections are used to determine the extent of the damage that may be expected and the resulting behavior of the airplane. The ditchings are made with flaps full-down, at landing attitudes ranging from 4-degrees to 12-degrees, and speeds ranging from 81 to 118 mph. Transports give better ditchings than bombers because there is less damage and the decelerations are lower. However, transports carry more people and passengers are normally untrained in ditching procedure so the survival problem is more acute. In rough-water ditchings are made perpendicular to the waves more damage and violence may occur, depending on the choice of the ditching site and portion of the waves contacted. Supersonic High-Temperature Rocket-Jet Test Facility 1957 16mm, Silent, Color, 370ft., 10.25min Supersonic Jet Tests of a Simplified Wing Structure 16mm, Silent, Black & White, 60ft., 3min. Supersonic Jet Tests of a Simplified Wing Structure 1957 16mm, Silent, Black & White, 180ft., 5min. Supersonic Jet Tests of Insulating Panels (Double Wall Construction) All I-B Models 16mm, Silent, Color, 240ft., 10min. Swing Arm Erector (SABER) concept for Single Astronaut Assembly of Space Structure 1985 16mm, Silent, Color, 400ft., 6min. T.F. #11 Wind Tunnel Tests of the U.S.S. Akron 16mm, Silent, Black & White T.F. #9 Free Spinning Tunnel 16mm, Silent, Black & White T.F. No. 10; Compressibility Experiment investigation of aerodynamic phenomena affected by compressibility. 16mm T.F. No. 2; Air Flow and Flow Separation 1935 16mm Presents nature of air flow and flow separation by titanium tetrachloride smoke pictures about a circular cylinder and airfoils. Tests were made in 2-foot smoke tunnel and a smaller tunnel. Depicts flow around a circular cylinder and a NACA0012 airfoil, along with a diagrammatic representation of the development of separation. Presents methods for the control of flow separation-rotating the cylinder so that the top moves downstream, thus deflecting the streamlines downward; introducing turbulence along a flat plate by use of the surface irregularities, as rivet heads; or using a small auxiliary airfoil ahead of the main one to obtain turbulence; controlling boundary layer by use of suction slots (NACA 2415 airfoil with flap used to illustrate this method). T.F. No. 24; Stability and Control Delta Wing Vertically Rising Aircraft 16mm, Silent, Black & White T.F. No.16 Parachute Stability Film 1947 16mm, Silent, Black & White Tailless Airplane Film 16mm, Silent, Black & White Take-Off and Landing Characteristics of a 0.13-Scale Model Convair XFT-1 Vertically Rising Airplane in Steady Winds 16mm, Silent, Color Take-Off and Landing of Logistics Transport Model in 6-Foot Waves 1957 16mm, Silent, Black & White/Color, 52ft., 1.5min. Take-Off Hydro-Skis 16mm, Silent, Color. 125ft., 5min. Take-Off Investigation Panto Base C-123--Part 2. 16mm Take-Offs and Landings--0.13-Scale Convair XFY-1 Vertically Rising Airplane in Steady Winds 16mm, Color, Silent, 10min Tank 2 A-26 16mm, Black & White, Silent Ditching tests were made in Tank #2 on a 1/12 scale model of the Army A-26 airplane at a weight corresponding to 25,730 lbs., full-scale, and with C.G. at 28.4% MAC and 5.1 in. (full-scale) above thrust line. Tests were made with nose wheel doors, bomb-bay doors, main landing-gear doors, aft end of nacelles, and lower turret-service door removed and with all-purpose nose door closed and braced open to act as a planning surface and stop diving at attitude angles of 3-degrees, 8-degrees, and 13-degrees; flap deflections of 0-degrees, 25-degrees, and 55-degrees; and speeds of 104, 118, 119, and 32 MPH, full-scale. Tank 2 A-26 Part 2 16mm, Black & White, Silent Ditching tests were made in Tank #2 on a 1/12 scale model of the Army A-26 airplane at a weight corresponding to 25,730 lbs., full-scale, and with C.G. at 28.4% MAC and 5.1 in. (full-scale) above thrust line. Tests were made with nose wheel doors, bomb-bay doors, main landing-gear doors, aft end of nacelles, and lower turret-service door removed and with all-purpose nose door closed and braced open to act as a planning surface and stop diving at attitude angles of 3degrees, 8degrees, and 13degrees; flap deflections of 0degrees, 25degrees, and 55degrees; and speeds of 111, 118, 123, 134, 132 and 141 MPH, full-scale. Tank 2 Ditching A-26 Part 1 16mm, Black & White, Silent Ditching tests were made in calm water in Tank #2 on a 1/12 scale model of the Army A-26 airplane with a weight corresponding to 25,730 lb. full-scale, c.g. at 28.4% MAC and 5.1 in. (full-scale) above the thrust line. Tests were made with the model undamaged; with bomb bay doors removed; and with bomb-bay doors, nose-wheel doors, main landing gear doors, lowered turret service door, and all-purpose door removed; with flaps deflected to 0 degrees, 25 degrees and 55 degrees; at attitude angles of 3 degrees, 8 degrees (landing angle), and 13 degrees (stall angle); over a full-scale speed range from 104 to 133 MPH. Tank 2 Ditching B-36 16mm, Black & White, Silent Ditching tests were made in calm water in Tank #2 with a 1/30 scale model of the Army B-36 airplane with 255,000 lbs weight, C.G. at 29% MAC and 3.61 ft. below deck line. Tests were made with no damage simulate; with bomb-bay doors and antenna housing failure simulate, with flaps simi-fixed, that is, free to swing upward into the retracted position upon contact with the water and the bomb-bay doors and antenna housing failure simulated, with the flaps rigidly fixed. The range of attitude angles for the tests was from 13-degrees to 5-degrees, flap setting range was from 0-degrees to 40-degrees, and the speed range was from 105 to 140 MPH. Tank 2 Ditching XP4M-1 16mm, Black & White, Silent Ditching tests were made in calm water at near normal landing attitude in Tank #2 with a 1/18 scale model of the Navy XP4M-1 airplane. Runs were made at 7-degrees attitude with no damage simulated; with the bomb-bay doors removed to simulate their failure; with the bombardier's windows, nose -wheel doors, forward entrance hatch, bomb-bay doors, radar housing, under-surface of the fuselage from the aft end of the bomb bay to station 680, rear entrance hatch, random, and jet propulsion intake covers removed to simulate their failure. The model weight corresponded to 55,000 lb.; C. G. was located at 22.4% MAC and 0.5 in. above thrust line flap settings were at 0-degrees, 20-degrees and 40-degrees; speed varied from 85.3 to 107.9 knots lengths of runs were from 9 to 3 times the fuselage length; and the maximum dececelerations varied from 4.0 4.5 g. Tank 2 Ditching XP4M-1 Part 3 Ditching tests were made in calm water at near stall landing attitude in Tank #2 with a 1/18 scale model of the Navy XP4M-1 airplane. The model weight corresponded to 55,000 lbs., C.G. was located at 22.4% MAC and 0.5 in. above thrust line, landing attitude was 13-degrees with respect to the water. For the tests, runs were made with no damage simulate; with the bomb-bay doors removed to simulate their failure, with the bombardier's windows, nose-wheel doors, forward entrance hatch, bomb-bay doors, radar housing, under surface of the fuselage from the aft end of the bomb-bay to station 680, rear entrance hatch, random, and jet propulsion intake covers removed to simulate their failure. The flaps were set at 0-degrees, 20-degrees, and 40-degrees; speed varied from 81.4 to 98 knots; length of runs varied from 2 to 8 times the fuselage length; maximum longitudinal decelerations varied from 2-8 times the fuselage length; maximum longitudinal decelera! Tank 2 Ditching XP4M-1 Parts 4 and 5 Ditching tests were made in calm water in Tank #2 with a 1/18 scale model of the Navy XP4M-1 airplane. Tests were made at 55,000 lbs. gross load with the navigator's escape hatch braced open to form a hydro flap at 45-degrees and 30-degrees with thrust line. These tests were made with no damage simulated,with bomb-bay doors removed to simulate their failure; and with bombardier's window, nose -wheel doors, forward entrance hatch, bomb-bay doors, radar housing, undersurface of the fuselage from the aft end of the bomb-bay to station 680, rear entrance hatch, random, and jet propulsion intake covers removed to simulate their failure. Attitude angles varied form 1-degree to 13-degrees; flaps were deflected to 20-degrees and 40-degrees; speed varied from 81.4 to 130.6 knots; length of runs were from 2 to 8 time the fuselage length; and maximum longitudinal decelerations were from 1.1 to 5.7 g. Tests were made at 80,000 lbs. gross load were made with ! Tank 94-F 1939 16mm Take-off and landing tests were made in Tank # 1 on NCA model 94-F, 1/10 scale which was designed by the Glenn L. Martin Co. and tested for the Bureau of Aeronautics. The model was free-to-trim on accelerated runs at 25 fps using gross loads of 128,000 and 121,200 lbs. Tank Boeing XPBB-1 1940 16mm Take-off and landing and stability tests were made in Tank# 1 on a 1/10-scale model of the Boeing PBB-1 flying boat, NACA 115, with gross weights of 41.7, 61.5 and 101.1 lbs.; C.G.'s at 25% and 35% MAC; at velocities from 5 to 21.1 fps; and trim angles from 3.1-degrees to 12.2-degrees. Model 115 had 9 in. deep step at station 45 and 7-degrees angle of afterbody keel. Model 115-A was tested with 1.10 in. deep step at station 46.4 and 7-degrees angle of afterbody keel and with short plastiline chines on tail extension. Model 115-A-2 had kicker plate at sternpost. Model 115-B had 11.1 in deep step at station 4.5 and 5-degree 50-foot angle of afterbody keel with short chines on tail extension. Model 115-B-1 had spherical tail turret and short chines. The spherical tail turret on model 115-b-1 had spherical tail turret and chines carried farther forward. Model 115-c had 1.1 in deep step at station 45.4 and 5-degree 50-foot angle of afterbody keel. It had strong yawing tendencies at 13.5 fps velocity. Two landing runs were made by model 115-C in rough water from 35 fps. Two take-off and landing runs were made by model 115-C at maximum seed of 55 fps. Flow around tail at low speed was shown for all models. Tank Glass Bottom Boat 16mm Tank Glass Bottomed Hull 1939 16mm Studies of flow along bottom of hull models 80-A, -B, -C, and -F with 3 depths of transverse steps and 1V-step were made in Tank #1. The models were accelerated and free-to-trim, simulating take-offs and landings, and the gross load coefficient for all runs was 0.5. Model 80-A had normal step depth; model 80-B, shallow step; model 80-C, deep step; and model 80-F, V-step. Landings of Models 80-A and 80-B were presented along with a bow wave for model 80-A. Tank Historical 1937 16mm Take-off tests were run in Tank #1 to obtain information on the water performance of the hulls and floats of 1/7.06 scale model Navy NC4 (NACA model 44) at 28,000 lb. gross load and 73 MPH getaway speed, 1/7.05 scale model Short Calcutta (NACA model 47) at 22,000 lb. gross load and 62 MPH getaway speed, 1/10.87-scale model Dornier Do.X (NACA model 54) at 1004, 000lb. and 76 MPH getaway speed and 1/5.25scale model Savoia-Marchetti 55X (NACA model 46) at 12,000 lb. and 77 MPH getaway speed. General views of these seaplanes are presented along with views of the hull models. Tank Investigation Bur. Aeor. Design DR-56 16mm Tank Investigation Bur. Aero. Design DR-56 Part IV 16mm, Silent, Black & White Tank Investigation of a 1/10-Size Model of a Martin Long-Afterbody Flying Boat- Part 1; Model 305 16mm Tank Investigation of a 1/20-Size Model of a Martin-Long Afterbody Flying Boat- Part 2; Model 305A 16mm Tank Investigation of the Hydrodynamic Characteristics of a 1/33. 33-Scale Jet-Powered Dynamic Model of the Martin XP6M-1 Flying Boat. 16mm, Silent, Black & White, 402ft, 16min Tank Model 104 1939 16mm Force tests were made in Tank #1 on PBY type outboard float and modification, 1/5 scale, NACA 104 series. Tested for Bureau of Aeronautics, Navy Dept. Models were loaded until deeply submerged then unloaded to emergence. Rectangular and lenticular streets were used for constant-speed runs at 15 and 25 fps and trim of 6-degrees . Model 104-A was the basic mode; 104-B had horizontal fins fore and aft; 104-C had fins aft only; 104-D had fins forward only. Model 104-A5 had modified bow and step added and was tested at accelerations of 15, 25, and 27.5 fps and loads ranging from 0 lb. to 52 lb. Tank Model 108 Boeing 314 1940 16mm Tank tests and tuft tests were made on a dynamically similar 9/100 scale model of Boeing 314 airplane (NACA 108) in tank #1. Various modifications were tested at gross weight 84,000 lb., with flaps at 0-degrees and 45-degrees, C.G.'s at 25% and 30% MAC, and with and without hydrostabilizers. Model 108 was original form with transverse main step 4.6 in. deep. Model 108-A had a main step moved aft 22.5 in. and depth of step 7.1in. Model 108-B was original form with breaker step, 2.8 in. deep, added on afterbody. Model 108-C had long afterbody extending sternpost 69.1in. Aft of original position. Model 108-D had original form with ventilation of main step. Model 108-E had afterbody raised to increase depth of original step to 7in. Model 108-F was same as -E with hook on afterbody tapering from 0 to4.2 in. depth at sternpost. Model 108-G had long afterbody raised to increase depth of original step to 9.7 in. Model 108-H had Vee-step 22.5 in. long with depth of step 9 in. at keel. Model 108-I had Vee-step 33.6in. Long with depth of step 11.1 in. at keel. Model 108-J was same as -I with point of Vee, 11.1 in. long cut flat and parallel with afterbody keel. Model 108-K had same step as -H with ventilation. Model 108-L had transverse main step moved aft with depth of step increased to 9 in. Model 108-M was same as -H with afterbody lowered to original position, with depth of step 7 in. at keel. model 108-p had original form with depth of step increased to 9 in. Model 108-Q was same as -P with step moved forward 1 station. Tuft tests were made to indicate the type of flow over the wing during accelerated runs with elevators full up and 20-degrees, flaps 0-degrees and 45-degrees. Spray characterizes tests were made of a midwing float during accelerated runs to 25 and 45 fps, at initial loads of 5.5 and 10.5 lbs. with trim angles of 1-degrees, 2 1/2-degrees, 5-degrees, 10-degrees, and 15-degrees. Tank Model 110 Consolidated 31X 1940 16mm Stability tests were made on 1/8 scale dynamically similar model of Consolidated Aircraft Corp. model 31X (NACA models 110-A, -B, -C, -D, -E, -E1, -K, and -L) in tank # 1. This seaplane in now know as the P4Y. The models were tested with original step position and with the step 8in. forward of the original position, at gross load of 50,000 lbs., with propellers discs and with flaps deflected 40-degrees. The elevator positions were neutral, 5-degrees up and full up and C.G.'s were ate 28% and 32% MAC. Model 110-B had flutes on the forebody; model 110-C had flutes and reflex chines on forebody; model 110-D had reflex chines on forebody. Model 110-E is the first modification of forebody lines, designated 31 -106; model 110-E1 is the first modification of forebody lines with depth step of 4.6% beam and No. 3 planning fin (0 deadrise, no flare) on afterbody. Model 110-K is second modification of forebody lines with No.3 planning fin on afterbody and depth of step 3.8% beam. Model 110-L is third modification of forebody lines with spacing of station of second modified forebody increased in ration 385/327 to increase length of forebody 58 in. the step depth is 3.8% beam. Tank model 113 1941 16mm Stability and spray characteristics tests were made in Tank # 1 on 1/2 scale dynamic model of PB2M-1 seaplane (NACA 113) with corresponding full-size characteristics of step location 558 in. aft of F.P., 8125 in. depth of step (5.015 beam), C.G. 70 in. forward of step (26.58% MAC), C.G. 146.7 in. above B.L., 1.366x10 [6th degree] slugs/sq.ft. pitching moment of inertia about C.G., and 30-degrees flap setting. Spray characteristics at gross loads of 120,000; 140,000; 160,000; and 180,000 lbs are presented during accelerated runs to 25 fps with stabilizers +3-degrees and elevators full up. Take-offs and landings at trims of 2-degrees, 4-degrees, 6-degrees and with elevators full up (full stall landing) showing spray and dynamic characteristics during accelerated runs and behavior when leaving water and making contact are presented for the same gross loads. The second run at each condition is with step ventilated to show its effect on behavior near the getaway speed. High-angle porpoising for gross load of 140,500 lb. at 37 fps showing flow over step and afterbody is also presented. Tank Model 116 1940 16mm Take-off and landing and stability tests were made in Tank #1 on a 1/8 scale dynamic model of Consolidated PB2Y-3 Flying boat, NACA 116. Model 116 had 15% increased wing area, wide chord elevators, stabilizers at -5-degrees and flaps at 40-degrees. Model 116-B-1 had L.E. slats, steps and chines added to tail, gross weight 128 lb., C.G.'s at 30% and 26% MAC, and elevators up and neutral. High-angle porpoising was obtained by jumping model to a trim above the upper limit. Model 116-B was tested with and without slats, without step or chines on tail, with elevators up and neutral, C.G.'s at 26% and 30% MAC., gross weights 108.6 lb. All tests were made by slowly accelerating over hump and take-off and landing runs.. Tank Model 116-E 1942 16mm Skipping and yawing tests were made in Tank #1 of a 1/8-scale dynamic model of PB2Y-3 seaplane (NACA model 116-E) with geometrically-similar plain wings, leading edge slats, increased-chord elevator, and flaps down 40-degrees. For skipping tests, models were free to rise and pivot about C.G., restrained in roll and yaw. Power-off landings simulated by accelerating model until airborne, trimming in air to desired attitude, then decelerating to rest. In all runs, landing trims are referred to hull baseline, loads are for full size seaplane, and positions of C.G. are in per cent to 5-degrees; 66,000 lb. load an C.G. at 28% MAC. Model 116E-2, with depth of step at keel 8in., was tested landing at 14-degrees to 2-degrees; 66,000 lb. load and C.G. 28% MAC. Model116E-4, with depth of step at keel 10in., was tested at landings at 11 1/2-degrees, to 4-degrees; 76,000, 56,000, and 66,000 lb. load; and C.G.'s at 28, 22, and 36% MAC. Model 116E-5, with transverse step 1/4 beam on either side of keel and 30-degree Vee at chines, was tested at lands 12-degrees to 4-degreesl loads 56,000 and 76,000 lb.; and C.G.'s 22, 28 and 36% MAC. Model 116E-6, with approximately 15-degree Vee step, was tested at landings 12-degree to 4-degrees, loads 56,000, 66,000, and 76,000 lbs.; and C.G. 28% Mac. Model 166F-3 original hull with wing incidence increased 4-degrees, was tested landing at 10-degrees to 2-degrees 66,000 lb. load and C.G. 28% MAC. Model 116E-7, with approximately 15-degree Vee step 1/4 beam on either side of keel and transverse step at chines, was tested landing at 11 1/2-degree to 6-degree; load 66,000 lb. and C.G. 28%. Model 116E-8, original model with 1 1/2 in. transverse spoiler 62 in. forward of step, was tested landing at 11 1/2-degrees to 4-degrees; load 66,000 lb. and C.G. 28% MAC. Model 116E-9, original model with 3 in. transverse spoiler 62 in. forward of step, was tested landing at 11 1/2-degree; load 66,000 lb. and C.G. 28% MAC. Yaw tests Made on model 116 E-3; with plain wing, no power, model free to rise and pitch about C.G., fixed in roll and yaw, elevators and rudders neutral, accelerated from 0 to 25 fps; at load 66,000 lb., C.G. 28% MAC. yaw extension; with tw0 9 hp motors driving 18 in. diameter, 3-balde propellers on inboard nacelles, flaps and ailerons down 40-degrees, elevators neutral, rudders movable from carriage, model free to pitch, rise and roll about C.G., free to yaw about point 4/34 in. aft of C.G., freedom in roll 1-degrees each side, freedom in yaw 1 1/2-degrees each side, at load 66,000 lb., C.G Tank Model 116-E3 Clippings 16mm Tank Model 116-E3 1942 16mm Depicts spray investigation of NACA model 116E-3, which is a 1/8 full-scale dynamic model of the PB2Y-3 airplane with motor driven propellers, in the NACA Tank #1. Throughout the tests the model is towed free to rise and pitch but is restrained in the roll and yaw; the flaps are at 0-degrees deflection; the elevators are full up; and the pivot and C.G. are at 28% MAC. The accelerations for the tests are 1/4 ft./sec./sec. and 1 ft./sec./sec. The modified models tested are the 116E-3f, which has the beam increased by adding horizontal planning bottom 1 ft. wide on each side of the hull and faired into the afterbody 39.3 ft. from the bow; the 116E-36, which has an increased beam extending 30ft. from the bow and not faired at the after end; and 116E-3h, which has 20-degrees down flare at the chine, obtained by adding a triangular strip at the chine. Tank Model 117 0A-9 1941 16mm Stability and control tests were made in Tank #1 on a 1/5-scale dynamic model of Grumman 0A-9 (NACA 117) amphibian, powered by tow 0.9 HP D.C. motors driving two 20 in. diameter, 12 in. pitch 2-blade propellers geared 3.29:1. Effects of propellers on spray and porpoising at various speeds and 0, 1/4, 1/2, 3/4 and full power are presented. Fore and aft movement of C.G. self-propelled at 30 fps and 35 fps for lower and upper limit porpoising are also presented. Tank Model 117 0A-9 1940 16mm Take off and landing tests were made in Tank # 1 on a 1/5 scale dynamically similar model of Grumman 0A-9 amphibian. The model is free to rise and pitch about it's C.G. The take-offs and landings were made at 6-degrees, 8-degrees, and 10-degrees trim and at some high angle; with elevators full up; with model speed range from 60 to 51 fps; with gross load of 63.4 lbs.; and with flaps at 30-degrees. Model 117 was original 0A-9 with depth of step 0.60 in. Models 117-C, C-1, and B had ventilated steps with slots in various positions. Model 117-A had afterbody raised to increase the depth of to .98 in. Models 117-E and G had 30-degrees and 20-degrees swallowtail steps. Model 117-H had a transverse step. Models 117-I and F had 60-degrees and 30-degrees notched steps. Model 117-D was same as 0A-9 with angle of forebody keel raised 2-degrees. Model 117-J was same as 0A-9 with chine strips removed from tail of hull. For model 117 suction in inches of water behind the step during accelerated runs is given at various distances from keel. Take-offs and landings of a full-size 0A-9 made on Back River of November 18-1940 are presented. Tank Model 124 1941 16mm Stability tank tests were made in Tank #1 on a 1/8-scale model of the Consolidated PBY flying boat (NACA 124) with 15% increased area for wing, slats on the wing L.E. and windmilling propeller for observing height of spray. Two runs are shown for all conditions; an acceleration of 25 fps in about 20 seconds, an acceleration to 25 fps in about 35 seconds, gross weight of 58.2 lbs and gross weight of 77.5 lbs. Elevators up and C.G. at 28% MAC for all conditions. Model 124 was standard airplane; 124-A had bow no. 1; 124-B had bow no. 2, and 124-C had bow no. 2 and breaker step on tail extension; 124-C1, 124-C2, and 124-C3 had bow no. 2 and breaker step on tail extension with 30-degrees, 45-degrees, and 20-degrees Vee main step, respectively. Tank Model 131 1943 16mm Take-off and landing tank tests of a 1/8 scale dynamic model of PB2Y-3 Seaplane (NACA 131) with increased power. The full-size conditions are: four 1800 hp engine, gross loads 76,000 lbs, flap deflection 20-degrees, and center of gravity 33% MAC. Take-off runs were at accelerations of 1, 2, and 3, ft./sec./sec. and landing trim angles ranged from 4-degrees to 12-degrees. Tank Model 132-4 PBN-1 1942 16mm Depicts tank tests of take-off and landing of NACA model 132-4, PBN seaplane, incorporating proposed change of step and tail extension. The accelerated run to take-off tests cover a take-off trim angle range from 8.5-degrees to 11.5-degrees; take-off speed range from 36 fps to 45.5 fps; landing trim angle range from 10-degrees to 14-degrees landing speed range from 33 fps to 42 fps; gross load range from 30,000 lb. to 40,000 lb.; with C.G. at 28% MAC; full power, 1/4 power, and no power; and with stabilizers down 3-degrees. The accelerated run to hump tests were made at 17.5 fps speed, C.G. at 28% MAC, full power, stabilizers 3-degrees and gross loads of 35,000 lb. and 40,000lb. Tank Model 133 1942 16mm Stability tests were made in Tank #1 of a 1/10 scale model of towed 12-place float wing amphibian glider (Naval Aircraft Factory, Plan 68696) NACA 133 with gross weight of 6.25lb.; C.G. 5.56 in. aft L.E. wing at center line and 3.8 in. above keel; pitching moment of inertia of 0.0987 slugs/sq.ft.; tow line 30 ft. long with forward end 10 in. above water; tow points 2.05, 1.33, and 2.86 in. above keel; elevators neutral, up 5-degrees or 10-degrees; flap step in design positions and deflected 5-degrees; modified bottom with flaps removed; same modified bottom with flaps down 5-degrees and cut off at main bottom; same modified bottom with flaps down to main step level (9.5-degrees), with and without skeg; at accelerated runs of Vmax from 31 to 40 fps. Tank Model 133 16mm Tank Model 134 16mm Tank tests were made in Tank # 1 on a 1/12-scale dynamic model of a 160,000 lb. flying-boat, NACA model 134, to study the effect of varying the dimensions of the afterbody. Tests were made with various loads, angles of afterbody keel, afterbody lengths, and with a pointed step, to determine their effect on landing and stability. Tank Model 139 Additional Tests 1942 16mm Stability tests were made in Tank #1 on a 1/10 scale model of a 24 place twin hull amphibian Navy glider (NACA 139). The full-size glider has a gross weight of 12,200 lbs.; C.G. aft of leading edge of wing at root at 60.8 in.; C.G. above keel at 47.5 in.; pitching moment of inertia of 29,768 slugs/sq.ft.; length of tow line 300 ft.; forward end of tow line 100 in. above water. For the model as tested the gross weight is 14.2 lbs.; C.G. aft wing leading edge at root 6.1 in.; C.G. above keel 5.1 in.; pitching moment of inertia 0.606 slugs/sq.ft. length of tow line 30 ft.; forward end of tow line 10 in. above water. The model is towed from towing post on center section of wing. The tests were run on all models with flaps at 0-degrees or 20-degrees; and elevators neutral, up 5-degrees, 10-degrees, and 15-degrees. Towing post lengths were 15 in., 12.4 in., 10.9., 9.4 in., 7.9 in., 6.4 in., 4.9 in., 3.4 in., and 0 in. (towing line attached to leading edge of wing). The maximum velocity range was from 25.4 to 42 fps. Tank Model 139 1942 16mm Stability tests were made in Tank #1 on a 1/10-scale model of a 24-place twin hull amphibian Navy Glider (NACA 139). The model is towed from a bridle attached at the bows; 1.68, 2.55, or 3.86 in. above keels or from a single line attached at the leading edge of the wing at the center line 6.31 in. above keels. The modes is tested with no flaps or flaps down 20-degrees; elevators neutral up 10-grees; with steps .25, 1.25, or .5 in deep; at gross weight 12.7-13.6 lbs; C.G. aft of leading edge of wing at root of 6.12 in.; C.G. 5.31 in. above keel; moment of inertia .483 slugs/sq.ft.; length of tow line 30-31ft.; forward end forward end of tow line 10 in. above water. The full size glider has a gross weight of 12,200 keel; pitching moment of inertia of 29,768 slugs/sq.ft. length of towline 300 ft.; forward end of towline 100 in. above water. Tank Model 139 Wing Tow Bridle Tests 1942 16mm Stability tests were made in Tank #1 on a 1.20-scale model of Navy (NACA 139) amphibian glider. The model is towed from a bridle attached to leading edge of center section of wing. The full size glider has a gross weight of 12,200 lbs.; C.G. aft of leading edge of wing at rood at 60.8 in.; C.G. above keel at 47.5 in.; pitching moment of inertia of 29,768 slugs/sq.ft.; length of tow line 300 ft.; weight was 13.9 lb.; C.G. aft wing leading edge at root 6.1 in.; C.G. above keel 5.1 in.; pitching movement of inertia 0.580 slugs/sq.ft.; length of tow line 30 ft.; forward end of tow line 10 in. above water. The tests were run with flaps at 0-degrees or 10-degrees; and elevators neutral, up 5-degrees and 10-degrees. Bridle lengths were 30, 26, 22, 18, 14, 10, and 6in. and the maximum velocity ranged from 29 to 46 fps. Tank Model 139-H 1942 16mm Towing tests of NACA seaplane model 139H were made in tank #1. Tank Model 140 Additional Tests 1942 16mm Take off tests were made in Tank #1 on a 1/10 scale model of a 12 place float wing amphibian glider (Allied Aviation Corp. Model 101-4) NACA model 140. The gross weight was 6.9 lbs; C.G. 16.8 in. aft nose and 4.07 in. above keel; pitching moment of inertia 0.0944 slugs/sq.ft.; tow line 30 ft. long; forward end of tow line 10in. above water; towing point 4.75 in. above keel line step 23.1in. aft of nose; flap deflections 0-degrees, 4-degrees, and 9-degrees; elevators neutral, up 5-degrees, 10-degrees, 15-degrees, 20-degrees and 25-degrees; and maximum velocities from 31 to 27.5 fps. Tank Model 140 16mm Tank tests were made in tank # 1 on a 1/10-scale model of a revised 12-place float-wing amphibian glider, Allied Aviation Corp. Model 101-4, NACA Model 140. Various modifications of the model were tested. Tank Model 140 16mm Tank Model 141 1942 16mm Stability tests were made in Tank #1 on 1/10-scale model of Navy 24 place seaplane glider LRG-1 (NACA 141) with gross weight of 14.51, 15,56, and 18.2 lb.; C.G. 4.6in. aft wing L.E. and 8.9 in. above keel; pitching moment of inertia 0.69, 0.74, and 1.12 slugs/sq.ft.; tow line 30 ft., long and forward end 10 in. above water; elevators neutral, up 2.5-degrees, 5-degrees, 10-degrees, 15-degrees, and down 5-degrees; flaps deflected 0-degrees and 20-degrees; at Vmax. from 28.8 to 37 fps. Model 141 was original model towed from nose of fuselage 11.9 in. above keel. Models 141-B and C had beam of floats increased 15%, tail angle increased 1-degree and were towed from bridle attached to bows 3.9 in. above keel line. Beam of Floats on model 141-E was 20% greater than original floats; tail angle was increased 1-degree floats were lowered 2 in.; planning surfaces full length of tail booms; towed from bridle attached to bows 5.9 in. above keel line. Model 141-f was the same as 141-D except chine flared was added to forebody. Close-ups of the tails of models 141-E-1 and 141-F-1 are presented. Tank Model 142 A-1 1942 16mm Resistance tests were made in Tank #1 on 1/40 scale model of Kaiser-Hughes cargo airplane-NACA 155A. The gross load was 400,000 lbs., getaway speed 85 MPH, and C.G 24.5% MAC, and the model was free to trim. Accelerated runs to getaway speed were made at 0.5 ft./sec [2nd power] and over hump speed at 0.25 ft./sec [2nd power]. Tank Model 142-A1 1943 16mm Tank tests were made to test the arrangement of hydrofoils on a 1/27-scale model of a 75 ft. motor launch (Hydrofoil boat-NACA models 142-A-1 and 142-B-1) in Tank #1. Displacements were 8.28 and 8.3lb.; hydrofoil incidences- forward 5-degrees, aft -1-degrees and 0-degrees; hydrofoil dihedral 20-degrees. Accelerated runs were made in smooth water from rest to 20 fps and constant speed runs were made at 15.1, 17.2, and 19.2 fps Tank Model 142-C 1943 16mm Tank tests were made to test the arrangement of hydrofoils on a 1/27-scale self propelled model of 75ft. motor launch (hydrofoil boat-NACA model 142-C) in Tank #1. Displacement was 8.83 lbs.; forward hydrofoils at 17 in. and 18.3 in ahead of stern; C.G.'s at 13 in., 13.9 in., 13.4in., and 15 in., ahead of stern; hydrofoil incidences - forward 0-degrees and aft 0-degrees, forward 2-degrees and aft 0-degrees, forward 4-degrees and aft 0-degrees, forward 4-degreesand aft -2-degrees, forward 5-degrees, and aft 0-degrees and forward 5-degrees and aft 4-degrees. Tests were run at constant speed varying from 9.3 to 19 fps. Tank Model 143 1942 16mm Tests were made in Tank #1 to determine the effect of various modifications on the landing stability of a 1/8 scale dynamic model of P4Y-1 (NACA 142) with full span slats; C.G. at 28% Mac; Stabilizers set -2-degrees to B.L.; gross weights of 89.2, 98.9 and 108.5 lbs.; flap deflections 20-degrees and 40-degrees and trim at landing range from 14-degrees to 4-degrees. Model 143 was basic model; 143-A had 1/4 in. increase in depth of step; 143-B had depth of step increased 1/2 in.; and 143-C had depth of step of basic model increased 3/4in. The area of ventilation ducts was 9.7, 6.4, 3.2, 1.5, 2.2, 3, and 4.5 sq.in. respectively for models 143-1, 143-2, 143-3, 143-4, 143-5, 143-6, 143-7, and 143-8. Tank Model 143-E (XP4Y-1) 16mm Resistance tests were made in Tank #1 on the NACA 143-E (XP4Y-1) with spray strips partial span flaps deflected 20-degrees, powered propellers at 4800 RPM and 8-degrees pitch loads of 98.9 lbs and 108.6 lbs, C.G. and 28% MAC and accelerations of 1 ft/sec/sec from 5 to 34 fps. Tank Model 152 1942 16mm Tank tests were made to test the arrangement of hydrofoils on a 1/27-scale model of 75 ft. motor launch (Tietjens type hydrofoil boat- NACA model 152) in Tank #1. Displacement was 8.5 lbs; hydrofoil incidences- forward 0-degrees, aft 0.5-degrees; C.G.'s 13.9 in. ahead of stern, 2.5 in. below deck and 11.8 in. ahead of stern, 2.5 in. below deck; tow pints- at keel near load water line and forward hydrofoil center strut at keel. Tests were run at constant speeds varying from 4.9 to 14.1 fps. Tank Model 158 1943 16mm Tank test of landings of a 1/16-scale model of the HK-1 cargo plane NACA 158-1 Landings were made with partial power; eight 4-blade, 1 ft. diameter dural propellers with 15-degree blade angle turning 3000 RPM; gross load of 109.2 lbs.; flap bow; at trims from 2-degrees to 14-degrees at 4 positions of the horizontal C.G., 20, 24, 28 and 32% MAC. For models 158-1 and 158-A with tail extension base circle diameters of 16.5 in. and 18 in. respectively; gross load of 98 lbs.; elevators at 20-degrees and horizontal C.G. at 24% MAC; spray pictures were made to show flow around stern during take-off and landings, with and without power. The effects of power on spray are shown with the flaps deflected 20-degrees, horizontal C.G. at 26% MAC, gross load of 97 lbs., using either 8 or 4 propellers during accelerated runs with and without power with elevators deflected 0-degrees or -20-degrees. Tank Model 158 Kaiser Hughes 1943 16mm Tank tests were made in Tank #1 on a 1/16-scale model of the HK-1 cargo seaplane (NACA 158-1) at gross load of 109.2, flap deflection 30-degree, vertical C.G. 14.83 in. above keel at step, step 59.88 in. aft of bow; showing flow behind step during high-angle porpoising at 30 fps with horizontal C.G at 32% MAC; flow behind step during accelerated run to take off with trim at take off 10-degrees and horizontal C.G. at 32% MAC; spray characteristics during accelerated runt o take off with horizontal C.G. at 24% MAC, flow behind step during a series of landings with horizontal C.G. at 32% at trim angles from 2-degrees to12-degrees; and landings at trims from 2-degrees to 13-degrees at horizontal C.G.'s at 24%, 28%, and 32% MAC. Tank Model 158-1 1943 16mm Tank tests were made in Tank #1 on low-speed bow spray in waves (2 and 3 in., approx.) and in calm water of 1/16 scale model of HK-1 (NACA 158-1). Test conditions were accelerated to hump speed and from 6-11 FPS; gross load 97 lbs. (counterweighted0; eight 4-blade 1 ft. diameter propellers with 15-degrees blade angle; flaps deflected 20-degrees; elevators deflected 0-degrees; C.G. at 28% MAC; power at 5000, 4000, and 3000 RPM. Tank Model 164 16mm Tank tests, giving spray characteristics, and take-off and landing tests were made in Tank #2 of a 1/12-scale model of the JRM-1 Cargo Seaplane (NACA model 164). Effects of power on bow and stern spray during accelerated runs are shown. Tests were run with horizontal center of gravity at 30% MAC, flaps deflected 30-degree and propellers turning at 4200 RPM. The gross loads were 82.5 lbs, horizontal centers of gravity 40% MAC and flap deflection 55-degrees, free-to-trim and fixed trim landings were made at trim angles of 3-degres to 10-degrees at decelerations of 1, 1.5, and 3 ft./sec./sec. and with horizontal center of gravity at 20% MAC at trim angles of 3-degrees to 80-degrees. Take-offs at accelerations of 1ft./sec./sec. were made with trim angles for 4.2-degrees to 9-degrees with horizontal center of gravity at 40% MAC. Tank model 165 B-2 1943 16mm Bow and stern spray characteristics tests were made in Tank #1 on the NACA model 165B-2 with arched forebody and after body and transverse step 1 in. deep at chines, [delta] [omicron] of 147.5 lb 976,000 lb. full-size), C.G. at 35% MAC. Accelerated runs were made at 1 ft/sec/sec to 25 and 30 fps. Tank Model 165 16mm Take off and landing (particularly landing) tests were made in Tank # 1 on a 1/8-scale dynamic model of the Consolidated PB2Y-3 with forebody lengthened 8.25-feet, and afterbody lengthened 4.75-feet, full-size. Step modifications are illustrated by Model 165-A using 30-degrees Vee production step with depth of step at keel 0.87-in; Model using 165A-1 using 30-degrees Vee unventilated step located at 1.40-inches forward of production step, with a depth of step at keel 1.53 in.; Model 165A-2 using transverse unventilated step located at the centroid of Model 165A-1, with depth of step at keel 1.14 in.; Model of 165-A3 using transverse unventilated step located at centroid of model 165A-2 with depth of step at keel 1.55 in. Landing trim angles range from 15.5-degrees to 5-degrees and landing speeds range from 35.5 fps to 60 fps. Gross landings were 147.5 lbs. 976,000 lbs, full-size), 166.5 lbs. 986,00 lbs, full-size0, and 186 labs (96,000 lbs, full-size). Spray pictures were give of Model 165A-1 with elevators neutral and 25-degrees up. Tank Model 165A 1943 16mm Depicts the NACA model 165A, which is a 1/8-scale model of the PB2Y-3 Seaplane, with the forebody lengthened 8.25 ft., and the afterbody lengthened 4.75 ft.. Throughout the tests the flaps are deflected 20-degrees, the center of gravity is 28% MAC, and the propellers are revolving at 6900 rpm. At no time is the towing speed higher that 30 fps. The gross loads used are 147.5 lb (76,000 lb, Full-scale) and 128 lb, (966,00, full-scale); the accelerations are 1ft./sec/sec. and 3 ft./sec./sec.; the elevators are in neutral and up positions Tank Model 180-1 1944 16mm Landing tests were made in Tank #1 on a 1/12 scale model of the JRM-1 flying boat (NACA model 180) modified for a gross load of 165,000 lbs. Tests were made on model 180-1 without power; with depth of step at keel 1.70 in., at centriod 1.35 in. (9% of the beam); rate of acceleration 1 ft./sec. [2nd power]; flap deflection 55-degrees; horizontal C.G. at 40% and 30% MAC; over trim angle range from 2.5-degrees to 10.5-degrees. Tank Model 189-1 1944 16mm, Silent, Black & White Spray characteristics tests were made in Tank # 1 on a 1/12-scale model of the JRM-1 flying boat (NACA model 180) modified for gross load of 94.3 lbs. With inboard spray strips on forebody, model 180-4 without and 180-5 with fillet in. Tests were made at full power and with propellers windmilling; with flap deflection 30-degrees; elevator deflection 0-degrees; horizontal C.G. at 28$ MAC.; rate of acceleration .75 ft./sec. [2nd power]; at gross loads of 94.3, 105.7, and 114.0 lbs. Tank Model 229, Part 2 1947 16mm, Silent, Color Second progress report on tests of NACA hydro-skis for high-speed airplanes. Take-off tests show that, for the speed range of 15-30 MPH full size (before the skis emerge), some water is drawn into the intake ducts on the original model. However, when the skis emerge, the spray is moving outward and only a few tray drops enter the ducts during this transition. The addition of a small strip extending only 3.4 in. full size from the fuselage keeps the spray clear of the intakes. Take-offs with the strips installed show that the water is now kept a considerable distance below the intakes during the critical 15 to 30 MPH speed range. The water is directed away from the model in addition to being kept below the intakes. The strips required to keep spray from entering the turbojet intakes are very small and presumably would have such a negligible aerodynamic effect that their retraction would not be warranted. Tank Model 229; Part 1 1947 16mm An investigation of the opportunities opened for the seaplane by jet propulsion is now under way at Langley Laboratory. This film is a progress report on a part of this investigation, tests of NACA hydro-skis for high-speed airplanes, which has shown marked possibilities. A 1/2-scale dynamically similar model of a hypothetical airplane, representative of current thought on high speed design is being used for the investigation. The fuselage form chosen for the airplane is such that turbojet and rocket powered plants could exhaust at the rear, and a possible turbojet intake location is shown on the top of the fuselage. NACA twin-ski arrangement hydro-skis, curved to permit flush retraction into the fuselage, are retractable planning surfaces extended below the airplane during take-off and landing and retracted in flight to eliminate their drag. The area of the skis is no more than 1/3 the area required for snow skis. For the take-off tests, the model is attached to the towing carriage of Tank #2 so that it is free to move vertically and to pitch about it's center of gravity; it has a gross weight corresponding to 13,140 lbs; floats with the wing tips slightly under the water and the wings thus provide lateral stability; runs as a displacement body, until a speed corresponding to 40 MPH full-size is reached, hen the hydro-skis emerge from the water; from this speed to take-off (148 MPH) the model rides on the hydro-skis; and the entire take-off is stable even though controls are fixed. It is assumed that the airplane has consumed fuel until its weight is reduced to 8,740 lbs. before landing, and for the landing tests, the model weight is reduced accordingly. The mode is catapulted; from the seaway catapult at Langley Field, Va., over open water as a free body and lands without benefit of longitudinal or lateral control such as a pilot could apply. On landing, the model rides on the hydro-skis until it decelerates to a speed considerably lower than the take-off emergence speed before dropping to a level where it is supported by buoyancy. The stability in roll during landing is very good. Waves up to 2 ft. high full-size have a very slight effect on the landing characteristics. The resistance during take-off is great enough to require the use of JATO. With a reasonable amount of research the resistance could be reduced sufficiently to eliminate the need. Many phases of research on hydro-skis are yet to be done; however, the results from preliminary experiments show that their use makes possible the design of an airplane that is extra-ordinarily clean aerodynamically and is capable of taking off and landing in any sheltered body of water. Tank Model 77K-1 16mm Presents resistance tests made in NACA Tank #1 for Bureau of Aeronautics, Navy Department, on NACA Models 77K-1, 77K-A and 77K-B. Two sizes of model 77K-1 are used, one being 1/10 scale, the other 1/10.8-scale. All models were tested under the following conditions: C.G. 5ft. 1 3/4 in. forward step, 11 ft., 10 3/4 in. above keel; gross load 129,550 lb.; getaway speed 78.3 knots; no thrust moment; and C.G. 5ft. 5 7/8 in. forward step, 12 ft. 2 1/2 in. above keel; gross load 122,523 lb.; getaway speed 71.9 knots; no thrust moment. All were accelerated from rest to getaway speed. For model 77K-1, 1/10-scale, the tachometer reading previously mentioned tests this model was tested at C.G. 5 ft. 2 1/4 in. forward 165,000 ft. -lb. thrust moment was accelerated slowly over hump. For the1/10.8-scale of model 77K-1 the tachometer readings must be multiplied by 1.61 to obtain full scale speed in knots and tests were run at C.G. 4 ft. 11 7/8 in. forward step, 9 ft. 11 7/8 in. above keel; gross load 130,000 lb.: getaway speed 86.9 view pictures showing action of bow at low speeds in waves for models 77K-A and 77K-B are presented. Tank Model 94, 94A, 94D 1939 16mm Take-off and landing tests were made in tank #1 on 1/10-scale NACA models 94, 94A, and 94D, designed by Glenn L. Martin C. and tested for the Bureau of Aeronautics, Navy Department. Free-to-trim, accelerated runs to take-off and landing through hump speed were made for models 94 and 94A at gross loads of 129,550 lb. and 1223,523 lb., with damping applied and no thrust moment. For model 94D, the gross load was 129,550lb., damping was applied and for the run to take off and landing there was no thrust moment applied, but on the run through hump speed, 173,000 ft.-lb. thrust moment was applied. Tank Model 16mm Depicts spray investigation of several modifications of the NACA model 116E-3. 116E-3i had the original beam increased 8 in. on each side. Model 116E-3j had 30-degrees down flare at chine starting 5.3ft. from bow. Model 116E-3k had 30-degrees down flare starting 2.7 ft. from bow. Model 116E-3k was tested with elevators neutral and 15-degrees down, and full up. All models were tested at gross loads of 66, 000 and 72,500 lbs. and accelerations of 1/4 and 1 ft/sec/sec. Tank Model PB2Y-3 Airplane with Simulated Jet Motors 1943 16mm Take off tests of a 1/8 size dynamic model of PB2Y-3 seaplane (NACA models 131J, 131J-1, 131J-2) with simulated jet motors were made in Tank #1. The full scale conditions were: four 1200 hp engines, gross load of 76000 lb., flap settings 40-degress and center of gravity at 30% MAC., Model 131J was tested with 3 Jets in sternpost directed aft and down 15-degrees to baseline of model; and model 131J-2 wihth 1 jet in sternpost directed aft, 1 jet each side of afterbody directed 7-degress out from plane of symmetry, all parallel to baseline. All models were accelerated to take off with and without jet power. Tank PBN-1 Flying Boat 1943 16mm, Black and White, Silent In order to study the effect of bow modification on the spray characteristics at the nose, investigations were made of the low speed bow spray of the 1/8 scale model of the navy PBN-1 seaplane. The center of gravity of the model was at 28% MAC and the tests were run at full power with elevators neutral. Tests were run on the model with the original PBN-1 bow and with such modifications as: the PBN-1 bow with chine strip; PBN-1 bow with chine strip extended full width aft to the propellers; and 30-degrees down flare; and PBN-1 bow with chine strip at nose and original chine flare increased to 30-degrees but with no increase in beam. Simulated loads were 30,000; 32,000; 35,000; and 37,000 lbs. Simulated loads were 3,000 lbs greater than actual loads so the results are conservative. The model was tested with 2.35 lb-ft (9,620 lb-ft, full-scale) negative pitching moment. Tank Tests of a 1/8-Scale Model of a Grumman JRF-5 Amphibian Fitted with Hydro-Skis 1950 16mm, Silent, Black & White, 272ft, 11min Tank Tests. Bru. Aero. Design DR-77 (Hydro-Ski Seaplane -Part 1) 16mm, Silent, Black & White Tank Ventilated Circular Chine 1942 16mm Tests were made in Tank #1 on ventilated circular chine of 48 in. length, 16 in. beam, 22.5-degrees deadrise, 2in. radius, 40 lb. displacement and 0.266 coefficient. Tests were made with no ventilation, ventilation, ventilation though slot 4, and through slots 3 and 4 at trim angles of 3-degrees and 6-degrees. The models were put in the water at 20 fps and 15 fps and accelerated to 40 fps. Separation of water at chine during take-off and landing is induced or aided by ventilation of chine, that is, by air flowing out of the side of the hull through longitudinal opening, or slots, along the chine. Tank XPB2Y-3 16mm Stability tests of 1/8 scale dynamic model of the consolidated PB2Y-3 Seaplane (NACA 116) were made in Tank #2 with stabilizers -5-degrees, flaps 40-degrees, 15% increased wing area, and wide chord elevators. The accelerated runs to 25fps in about 30 seconds were made with center of gravity at 28% MAC; elevators neutral and up; and at loadings of 128 lbs (66,000 lbs. full-size), 137.7 lbs (971,000 lbs full size) 147. 4 lbs (76,000 lbs, full-size) 157.1 lbs (81,000 lbs. full-size), and 166.8 lbs, (86,000 lbs, full size) Tank-Historical Clippings 16mm, Silent, Black & White TBF-1 Wing Fabric Deflection 16mm Presents tests made in the 16-Foot high-speed tunnel showing fabric deflection of the alieron of a TBF-1 airplane. Fabric depression tests were run at an angle of attack of -1.2-degrees, alieron deflection angles of -18.7-degrees to 0-degrees and induced velocities of 160 to 335 MPH. Aileron stalling and wing buffeting tests were run at angles of attack of 3.4-degrees and 8-degrees, aileron deflection angles of -19.4-degrees to -3.3-degrees, and induced velocities of 160 to 310 MPH. Fabric bulge tests were run at angles of attack of -1.2degrees and 8-degrees aileron deflection angles of 5-degrees to 18.3-degrees, and induced velocities of 160 to 335 MPH. Deformation of the wing skin occurred under high aerodynamic loads. Technique for the Simulation of Lunar and Planetary Gravitation Fields Including Pilot Model Studies 1963 16mm, Silent, Black & White, 225ft., 6min. Technology for Safer Aircraft (1974 Inspection Film) 16mm, Sound, Color 600ft., 17min. Technology Utilization 1970 16mm, Sound, Color, 949ft., 26.5 Test of a United Aircraft Corp. Inlet Model on Langley's Mach 6 11-Inch Ceramic-Heated Tunnel 1960 16mm, Silent, Black & White, 570ft., 15min. Test of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2 1957 16mm, Silent, Color, 110ft., 3min. Test of All Metal High Temperature Landing Gear Wheel at Landing Loads Track 1959 16mm, Silent, Black & White, 30ft., 1min. Test of Full Scale X-15 Horizontal Stabilizer in 9-by-6-Foot Thermal Structures Tunnel 1958 16mm, Silent, Black & White, 195ft., 5.5min. Test of Full-Scale X-15 Horizontal Stabilizer in 9- by 6-Foot Thermal Structures Tunnel (Run no. 58-54 and 58-55; Camera No. 8; Angle of Attack 0-Degrees and 5-Degrees); 1958 16mm, Silent, Color Test of Full-Scale X-15 Horizontal Stabilizer in 9- by 6-Foot Thermal Structures Tunnel (Run no. 58-55; Camera no. 2 S-22; Angle of Attack 5-Degrees) 1958 16mm, Silent, Black & White Test of Full-Scale X-15 Horizontal Stabilizer in 9x6' Thermal Structures (Run no. 58-54; Camera no. 1S-21; Angle of Attack--0). 16mm Test of Full-Scale x-15 Horizontal Stabilizer in 9x6' Thermal Structures Tunnel (Run no. 58-54; Camera no. 2S-22; Angle of Attack--0). 16mm Test of Full-Scale X-15 Lower Movable Vertical Stabilizer in 9-by 6-Foot Thermal Structures Tunnel 1959 16mm, Silent, Black & White, 340ft., 9.5min. Test of Insulation Shield for Centaur in the 9- By 6-Foot Thermal Structures Tunnel 1962 16mm, Silent, Black & White, 70ft., 2min Test of the Second Cambridge Research Center Sounding Rocket at Wallops Island, Va. 1958 16mm, Silent, Color, 245ft., 6.5min. Test of Vortex-Ring Parachute at Supersonic Speed in the Langley Unitary Plan Wind Tunnel 1960 16mm, Silent, Black & White, 39min. Test Run in Laboratory Scale Ceramic Heated Jet (Beryllium, Beryllium-Cooper, Titanium) 1957 16mm, Silent, Color, 110ft., 3min. Test Specimen Run in the Pilot Ceramic Heated Jet 1957 16mm, Silent, Color, 140ft., 4min. Testing of the DS-1 Structural Concept Model (Boeing Airplane Company-Seattle, 24 Washington) 1962 16mm, Silent, Color, 9min. Tests 1/10th Convair YF-102 (MX-1554) 16mm Tests Army Chemical Chords 14"" Parachute in 7x10 16mm, Silent, Black & White Tests of 1/5 Scale Model Fairchild M224 VTOL Research Airplane (Army Designation VZ5FA) in the NACA Langley 300-MPH 7X10 Foot Tunnel 1956 16mm, Silent, Black & White, 390ft., 11min. Tests of a 1/40 Scale Model of the Douglas MX-656 Airplane in the Langley 20-Foot Spin Tunnel 16mm, Silent, Black & White, 237ft. Tests of a 1/40-Scale Model of the Douglas MX-656 Airplane in the Langley 20-Foot Spin Tunnel 16mm, Silent, Black & White Tests of a 1/4-Scale Model of the Republic Aircraft Corp., Escape Capsule in the Langley 20-Foot Free Spinning Tunnel 1957 16mm, Silent, Black & White, 600ft., 16min. Tests of a 1/5-Scale Model of the Ryan X-12 Airplane on Langley Control Line Facility 1956 16mm, Silent, Black & White, 415ft., 11.25min. Tests of a Phenolic Nylon Panels Bounded to Metal (Conducted in Co-Operation with Douglas Aircraft Co., in Langley 11-Inch Ceramic Heated Tunnel) 1961 Originally recorded in 16mm, Silent, Color, 1350ft., 37.5min. Tests of a Rotoschute with NACA 0015 Blades at Constant Tunnel Airstream Velocities 16mm, Silent, Black & White Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2 1958 16mm, Silent, Black & White, 395ft., 11min. Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2 1958 16mm, Silent, Black & White 380ft, 10.5min. Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2. (Five Aluminum-Alloy Models of 20-Inch Chord with 0.064-Inch-Thick Skin, 0.025-Inch-Thick-Webs, and Various Chordwise Stiffening at 2-Degree Angle of Attack) 1959 16mm, Silent, Black & White, 355ft., 10min. An experimental study was made on five 2024-T3 aluminum-alloy multiweb wing structures (MW-2-(4), MW-4-(3), mw-16, MW-17, and MW-18), at a Mach number of 2 and an angle of attack of 2 deg under simulated supersonic flight conditions. These models, of 20-inch chord and semi-span and 5-percent-thick circular-arc airfoil section, were identical except for the type and amount of chordwise stiffening. One model with no chordwise ribs between root and tip bulkhead fluttered and failed dynamically partway through its test. Another model with no chordwise ribs (and a thinner tip bulkhead) experienced a static bending type of failure while undergoing flutter. The three remaining models with one, two, or three chordwise ribs survived their tests. The test results indicate that the chordwise shear rigidity imparted to the models by the addition of even one chordwise rib precludes flutter and subsequent failure under the imposed test conditions. This paper presents temperature and strain data obtained from the tests and discusses the behavior of the models. Tests of an Annular-Jet Ground Cushion Device Over Water 1959 16mm, Silent, Black & White, 310ft., 8.5min Tests of Beryllium and Copper Hemispherical-Nose Models in Cooperation with Lockheed Aircraft Corp. and U. S. Navy 1958 16mm, Color, Silent, 120ft., 3.5min. Tests of Beryllium and Copper Hemispherical-Nose Models in Cooperation with Lockheed Aircraft Corp. and U.S. Navy 1958 16mm, Silent, Black & White, 325ft., 9min. Tests of Copper Hemispherical Models for Lockheed Aircraft Corp. in Cooperation with U.S. Navy Polaris Project 1958 16mm, Silent, Black & Color Tests of Dynamic Scale Model of Gemini Capsule in the Langley 20-Foot Free-Spinning Tunnel with and without Drogue Parachute 1962 Originally recorded in 16mm, Silent, Black & White, Tests of Falcon GAR-3 Sealing Sleeves in the 9- by 6-Foot Thermal Structures Tunnel 1959 16mm, Silent, Color, 6330ft., 3hrs. Tests of Fins for Tart Missile in the 27- by 27-Inch Nozzle Preflight Jet Test Facility; May 7 and 8, 1958 0958 16mm, Silent, Black & White Tests of Fins for ""Tart"" Missile in the 27- by 27-Inch Nozzle, Preliminary Jet Test Facility 1958 16mm, Silent, Black & White Tests of Graphite and Graphite Mixtures in 700-KW Arc Powered 1958 16mm, Silent, Black & White, 335ft., 24min. Tests of Ground-Effect Machines Over Water 1959 16mm, Silent, Black & White, 300ft., 8.25min. Tests of Hemispherical Beryllium Oxide and Beryllium Oxide-Beryllium Models in the Pilot Model Ceramic Heated Air Jet in Cooperation with U.S. Navy Polaris Project 1958 16mm, Silent, Color, 410ft., 5min. Tests of Hemispherical Beryllium Oxide Model in Pilot Model Ceramic Heated Jet in Cooperation with U.S. Navy Polaris Project 1958 16mm, Silent, Black & White Tests of Hemispherical Models for Douglas Aircraft Company (Tests Conducted in Pilot Model Ceramic Heated Air Jet) 1958 16mm, Silent, Black & White, 600ft, 17min. Tests of Materials for Polaris Project in Cooperation with U.S. Navy (Performed in LAL Laboratory-Scale Ceramic Heated Air Jet Facility) 16mm, Silent, Color Tests of Materials in Langley Pilot Model Ceramic Heated Air Jet for U.S. Navy Special Projects 1959 16mm, Silent, Color, 230ft., 6.5min. Tests of Nose and Probe Models of Various Materials in Pilot Model Ceramic Heated Air Jet for Nike-Zeus Project in Cooperation with U.S. Army Picatinny Arsenal 1958 16mm, Silent, Color, 750ft., 21min. Tests of Nose Models for U.S. Army Nike Zeus Program in Cooperation with Douglas Aircraft Company, Inc 1958 16mm, Silent, Black & White Tests of Nose Models of Various Materials in Laboratory-Scale Ceramic Heated Air Jet in Cooperation with Boeing Airplane Company 1959 16mm, Silent, Black & White, 1615ft., 44min. Tests of Nose Models of Various Materials in Laboratory-Scale Ceramic Heated Air Jet in Cooperation with Boeing Airplane Company 16mm, Silent, Black & White, 900ft., 25min. Tests of Preliminary Hysail Model in the 4- by 4-Foot Supersonic Pressure Tunnel; Nozzle set for M=20 (Actual Mach No. 1.86; Stagnation Pressure 1.0 to 1.5; 48 Frames Per Second); 1958 16mm, Silent, Black & White Tests of Reentry and Other Type Vehicles in the Langley Vertical Spin Tunnel 1959 16mm, Silent, Black & White, 190ft., 5.5min. Tests of Several Types of Landing Skid Materials Made at NASA Landing Loads Track. 1959 16mm, Silent, Black & White, 320ft., 9min. Tests of the Aeronautics CVWS Missile in the Langley 16-Foot Transonic Tunnel 1959 16mm, Silent, Black & White, Tests of Vortex-Ring parachute at Supersonic Speed in the Langley Unitary Plan Wind Tunnel 1960 Originally recorded in 16mm, Silent, Black & White, 306ft., 8.5min. The Ablation of Pyrolytic-Coated Graphite in the 700-kw Arc-Powered Jet. 1959 16mm, Silent, Black & White 445ft., 12min The Air We Breathe 16mm, Silent, Black & White The Arc Image Furnace 1958 16mm, Silent, Color, 255ft., 7min. The Behavior of Bell Aircraft Corporation Hypersonic Leading Edges in Arc-Powered Facilities of the NASA Structures Laboratory 1960 16mm, Silent, Color, 4116ft., 114min. The Behavior of Spinning Membranes Under Gyroscopic Loading in Moderate Vacuum 1961 16mm, Silent, Black & White, 55ft., 1.28min. The DC-10 Graphite Epoxy Rudder 1981 16mm, Sound, Color, 16min. The Effect of Various Bow Modifications on the Hydrodynamic Characteristics of a 1/13.33-Scale Dynamic Model of the Martin P6M-2 Seaplane 1958 16mm, Silent, Black & White The Effect of Various Bow Modifications on the Hydrodynamic Characteristics of a 1/13.33-Scale Dynamic Model of the Martin P6M-2 Seaplane 1958 16mm, Silent, Color, 950ft., 26min. The Flying Seat; Bell Rocket Belt & Seat 16mm, Silent, Color 12min. The Foot-Controlled Maneuvering Unit 1976 16mm, Sound, Color, 580ft. The Highest Honor (HQ-81) 1963 16mm, Sound, Color, 624ft., 17.5min The Hydrodynamic Characteristics of a Submerged Lifting Surface Having a Shape Suitable for Hydro-Ski Application 1959 16mm, Silent, Black & White, 185ft., 5min. The Inside of Arc Welding-Overhead Position 1942 16mm, Sound, Color The Lockheed YF-12 16mm, Silent, Color The Lunar Orbiter: A Spacecraft to Advance Lunar Exploration Originally recorded in 16mm, Silent, Color, 300ft., 8min. The NACA Combined Load Testing Machine 16mm, Silent, Color, 250ft., 7min. The Ranger Program. Simi-Annual Report Number 15 1965 16mm, Sound, Color, 476min., 13min. The Scout 16mm, Silent, Color The Scout 16mm, Sound, Color The Second Flight Test of the Parachute Recovery System of the Temco Corvus Missile at Wallops Island, Va 1959 16mm, Silent, Color, 225ft., 7min. The Study of Man's Capability for Self Locomotion on the Moon 1968 16mm, Sound, Color, 18min. The Supersonic Transport in the Air Traffic Control System 1965 16mm, Sound, Color, 662ft., 18min. The XF-88B Propeller-Flight Research Program (Flight Tests on Supersonic Propellers) 1957 16mm, Silent, Color, 140ft., 4min. Thermo-Lag Ablation Tests 1960 Originally recorded in 16mm, Silent, Color, 1130ft., 31min. Thiokol Solid-Fuel Ram-Jet Tests in Preflight Jet 16mm, Silent, Color Third Parachute Recovery Test of a Full-Scale Model of the Temco Corvus Missile at Wallops Island, VA; 1959 16mm, Silent, Color, 235ft., 5.6min. This Is NASA Speech Film 1967 (Axel Matson Col. Pos. Snd. 731') 1967 16mm, Sound, Black & White/Color, 20min Thor Oscillations Due To Ground Winds 1965 16mm, Silent, Black & White, 140ft., 4min. Three and a Quarter Inch Test Rockets Fired for Melpar, Inc. 1957 16mm, Silent, Color, 90ft., 2.5min. Title of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2 1957 16mm, Silent, Black & White, 380ft., 10.5min Toronto 16mm, Color Tow Model 1942 16mm Depicts flights in the full-scale tunnel of a 5ft. span model of the Bristol target glider. Tow Tests of a 1/3.8-Scale Model of a Paraglider Air Cargo Delivery System in the Langley Full Scale Tunnel 1962 16mm, Silent, Color, 150ft., 4min. Toward Aircraft of the Future (1974 Inspection Film) 1975 16mm, Sound, Color, 760ft., 21min. Towing In Full Scale Tunnel Square Planform Paraglider 2nd) Tow Point Too High 3rd) Tow Point Too Low 1961 Wind tunnel tests Tracking Films of Two Hugo Nike Cajun Hurricane Photographic Rockets Fired December 5, 1958 from PARS, Wallops Island, VA 1959 16mm, Silent, Color, 580ft., 16min. Transition Between Ramp and Water of a 1/10-Scale Model of the F-86 Airplane Equipped with Hydro-Skis-- Part I 16mm, Silent, Color, 145ft., 4min. Transition Flight Tests of a Low Wing Transport Vertical Take-Off with Tilting Wing and Propellers 16mm, Silent, Black & White Transition Flight Tests of a Vertically Rising Model Similar to Lockheed XFV-1 16mm Transition-Flight Investigation of a Four-Engine Transport Vertical Take-Off Airplane Model Utilizing a Large Flap and Extensible Vanes for Redirecting the Propeller Slipstream. 1957 16mm, Silent, Color, 165ft. 4min. Transonic Aeroplasticity Investigation of Models of the Dyna-Soar Booster (Titan 11) Fins in the Langley Transonic Blowdown Tunnel 1961 16mm, Silent, Black & White, 240ft., 11.5min. Transonic Flutter Investigation of Dynamically and Elastically Scaled Model of the Grumman F11F-1 Airplane Wing with Simulated 150-Gallon Fuel Tanks Attached by Means of Flexible Pylons 1958 16mm, Silent, Black & White Transonic Flutter Tests of Cantilevered Mounted Models of the Bell D188A Airplane Wing in the Langley Transonic Blowdown 1959 16mm, Silent, Black & White, 110ft., 3min. Transonic Flutter Tests of Cantilevered Mounted Models of the F-104A T-Tail in the Langley Transonic Blowdown Tunnel 1958 16mm, Silent, Black & White, 210ft., 6min. Transonic Flutter Tests of F-103 Vertical Tail Models in Langley 26-Inch Transonic Blowdown Tunnel 1957 16mm, Silent, Black & White, 224ft., 6min. Transonic Flutter Tests of Model of the Y-P6M T-Tail in Langley Transonic Blowdown Tunnel 1958 16mm, Silent, Black & White Transonic Flutter Tests of Models of McDonnell F-101A Wing in Langley Transonic Blowdown Tunnel 1957 16mm, Silent, Black & White, 820ft., 23min. Transonic Flutter Tests of Models of Republic F-105B Wing with External Stores in the Langley Transonic Blowdown Tunnel 1958 16mm, Silent, Black & White Transonic Flutter Tests of Models of the Martin-Bell Dyna Soar Vehicle in the Langley Transonic Blowdown Tunnel 1959 16mm, Silent, Black & White, 110ft., 3min. Transonic Flutter Tests of the F-105B Vertical Tail Model in the Langley 26-Inch Transonic Blowdown Tunnel (Model with Two Dampers Installed) 1957 16mm, Silent, Black & White, 100ft., 4min. Transonic Flutter Tests of Y-P6M T-Tail in the Langley Transonic Blowdown Tunnel 1958 16mm, Silent, Black & White Tuft Grid Mounted Behind 60-Degree Delta Wing Model 16mm, Silent, Black & White, 80ft., 2min. Tuft Grid Survey Behind a 6-Inch diameter Cylinder Made in the Langley Stability Tunnel (Tufts 1 Inch Apart and 3 Inches in Length) 1959 16mm, Silent, Black & White, 440ft., 12min. Tuft Studies Advent-Agena-Atlas Combination 1961 16mm, Silent, Black & White, 194ft., 5.5min. Tuft Studies G-17 16mm Tuft tests were made in the pressure, low-turbulence tunnel on the G-17 transition section with entrance lips #19 with RN of 2.4x10 [6th power], lift coefficients ranging from 0.03 to 1.23, Vn/Vo ranging from approximately 0.57 to approximately 0.76 and angle of attack continuously increasing from lift coefficient of 0.03 to stall. Tuft Studies of B-36 Part 2 16mm Presents tuft studies depicting air flow around a drooped nose wing-nacelle model of the B-36 airplane. Tests cover on airplane lift coefficient range from 0.275 to1.025 at an RN of 2.5x10 [6th Power]. Tuft Studies of Lockheed Wing # 3 1939 16mm Depicts tuft studies made on the Lockheed Wing # 3 in the 19-foot Pressure Tunnel. The tests were made at a density of approximately 70 pounds per square foot; flap deflections of 0%, 25%, 50%, 80%, and 100%; and an angle of attack range from 6-degrees to 20-degrees. Tuft Studies of Navy Wing # 1 16mm Depicts tests to determine stalling characteristics of NACA 230 series Navy tapered wing no. 1 in the 19-foot pressure tunnel. The tests were run at an RN of 4.66x10 [6th power] and with and without wing flaps. The Range of angles of attack of the wing without flaps was 11.1-degrees to 21.8-degress; for the wing with 53% span split flaps deflected at 60-degrees to the range of angles of attack was 9.6-degrees to 20.6-degrees; and for the wing with 90% span split flaps deflected 60-degrees the range of angles of attack was from 10-degrees to 20.2-degrees. Tuft Studies of Navy Wing # 4 16mm Depicts tests to determine stalling characteristics of NACA 230 series Navy tapered wing no. 4 in the 19-foot pressure tunnel. Tests were run at a RN of 4.8x10 [6th power] and with and without split wing flaps. The range of angles of attack of the wing with a 53% span split flap deflected 60-degrees was from 7.4-degrees to 19.7-degrees; and for the wing without flaps of the angle of attack range was 9-degrees to 20.4-degrees; and for the wing with 90% span split flaps deflected 60-degrees the range of angles of attack was 10-degrees to 19.7degrees. Tuft Studies of P-67 16mm Tuft Studies were made of the full-scale McDonnell P-67 outboard engine nacelles without power. The tests were run at 150 and 200 MPH indicated airspeed and angles of attack of 0-Degrees, 5-Degrees, and 9.5-Degrees with the inboard cooling flap positions at fully closed, high speed and fully open. Tuft Studies of XB-36 16mm Presents tuft studies depicting air flow around the inboard nacelle with air inlets at leading edge of the wing of the B-36 airplane. Tests cover a lift coefficient range of 0.153 to 1.075 at the RN of 2.5x10 [6th Power] Tuft Studies of XF4U-1 16mm Tuft studies were made on the wing of a 1/2.75 scale model of the F4U-1 airplane in the 19-foot pressure tunnel. Tests were run with no propeller, propeller idling, and propeller operating; slotted flaps deflected 50-degrees; ailerons drooped 10-degreees; V/nD=1.10, 0.75, and 0.45; q=13, 16, and 8 pounds per square foot, blade angles 17.5-degrees and 10-degrees; and angles of attack from 0-degrees to 22-degrees continuous. Tufts Studies and Canopy Ditching Tests X-181 TST 16mm, Silent, Black & White Tuft studies and canopy ditching investigations were made in the full-scale tunnel on the Grumman XF8F airplane. For the tuft studies, the airplane was in the service condition with the propeller removed. The tunnel airspeed was 63 MPH, flap deflections was 40-degrees, and the angle of attack range was 0-degrees to 27-degrees. The canopy ditching investigation was conducted to determine the action of the canopy when ditched by emergency release. Tests were made at airspeeds of 0, 63, and 100 MPH; and angle of attack 5-degrees. The force required to release the canopy decreased as air velocity increased. Turbine Blade Fabrication Using a Lost Wax Coring Technique 1962 16mm, Sound, Color, 185ft., 6min. Typhon Induction System 1960 16mm, Silent, Black & White, 885ft., 24.5min. Unitary Plan Wind Tunnel Tests of Cook Technological Center Parachutes in the Wake of a Conical-Nosed Cylindrical Body Having a Base Diameter of 2.375-Inches (6 Parts) 1962 Originally recorded in 16mm, Silent, Black & White, 4234ft., 1hour 59min. Unitary Plan Wind Tunnel Tests of Cook Technological Center Parachutes in the Wake of a Conical-Nosed Cylindrical Body Having a Base Diameter of 2.375-Inches (6 Parts); 1962 16mm, Silent, Black & White, Par 1 24.5 minutes 880 feet; Part 2 24 minutes 862 feet; Part 3 15 minutes 540 feet Part 4 16.5 minutes 603 feet Total 4234', 1hr. 59min. Unitary Wind Tunnel Tests of 30-Degree Conical Ribbon Parachute and a Rotofoil Parachute Towed in the Wake of a Conical Nosed Cylindrical Body 1962 Originally recorded in 16mm, Silent, Black & White, 880ft., 24.5min. United States Space Explorations 1958 1962 Originally recorded in 16mm, Silent, Color, 690ft., 19min. Unknown Film Sections 16mm, Sound, Color Unsteady Inlet Flows 16mm, Silent, Black & White V.D.T. Stall Control Wing 16mm V/STOL Aircraft- Campbell Presentation, April 1970 1970 16mm, Silent, Color, 587ft., 16.3min. V/STOL Aircraft 1967 16mm, Silent, Color, 1315ft., 36.5min. V/STOL Aircraft Research Film Supplement for NASA Committee on Aircraft Aerodynamics, June 1960 1960 16mm, Silent, Color, 650ft., 18min. Vacuum Sphere Tests of Allegheny Ballistics Laboratory X-248 Rocket Motor in Support of Thor-Able and Atlas-Able Test Programs 1960 Variable Sweep Wing Flutter Investigation in Langley Transonic Blowdown Tunnel 1961 16mm, Silent, Black & White, 400ft., 11.6min. Ventilated Flows with Hydrofoils 1959 16mm, Silent, Black & White, 115ft., 3min. Vertical Descent and Landing Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Still Air 16mm, Silent, Color Vibration Analysis Using Holographic Interferometry 1970 16mm, sound, Color 340ft., 9.5min Vibration and Flutter 16mm, Silent, Black & White Vibration and Flutter 16mm, Silent, Black & White Vibration Studies of a 1/5-Scale Model of the Saturn Launch Vehicle 1964 16mm, Sound, Color, 340ft., 9.5min. Vibration Tests of a Hydro-Ski-- P-40K Flight (Extra). 16mm Viking Sampler Arms 16mm, Silent, Color Vortex System Details For 1-G And 5-G Flights At Varying Angels Of Attack 16mm, Silent, Black & White, 9min Vosper Model Demonstration (Part I) 1949 16mm, Silent, Black & White Rough-water investigations were made, in Langley Tank #1, of the Vosper design P.TESTS. boat model. Tests were made without spray strips, in irregular waves of average height 5 in. and average length 17 ft.; and with spray strips in waves of average height 3.5 in. and average length 24 ft.; at velocities of 15, 23, and 30 ft./sec. VTOL Research Aircraft 1960 16mm, Silent, Color, 450ft. 12.5min VZ-2 Tilt Wing V/STOL Aircraft at Langley Research Center 1961 16mm, Silent, Black & White, 440ft., 12.5min. VZ-2 Wind-Tunnel Tests. Wing Tuft Flow Studies 1961 Originally recorded in 16mm, Silent, Color, 3150ft., 1hr. 29min. W 2F-A 2F Nose Wheel Shimmy Tests at the NASA Landing Loads Track 1960 16mm, Silent, Color, 1135ft., 31.5min. W.P. Manned Parawing Tests at Fort Bragg 1966 16mm, Color WADC Pressure Suit Component Tests in Wallops Island Pre-Flight Jet 1958 Originally Recorded in 16mm, Silent, Black & White, 40ft., 1min. Wake Surveys Tuft Grid Technique 16mm Water Channel Study 16mm Depicts flow visualization in variable density open throat tunnel by means of the 8x8 water channel. Show control of flow pulsation by the use of slots in the exit cone, use of a false wall in the entrance cone, and use of the proposed exit cone of the vertical tunnel as designed by the atmospheric tunnel staff. Water Film Cooling of 80-Degree Cone 1958 16mm, Silent, Color Water Immersion Techniques for Simulation of Mobility of an Astronaut in a Pressurized Suit under Conditions of Weightlessness 1964 16mm, Silent, Black and White, 380ft., 10.5min. Water Landing Characteristics of a 1/6-Scale model Reentry Capsule with an 80-Inch Heat Shield 1959 Originally recorded in 16mm, Silent, Color, 150ft., 4min. Water Landing Characteristics of a Reentry Capsule 1958 Originally recorded in 16mm, Silent, Color, 110ft., 3min. Water Landing Characteristics of Winged Missile 1966 16mm, Silent, Black & White, 220ft., 6min. Water Pressures and Accelerations During Landing of a Dynamic Model of the Apollo Spacecraft with a Deployed Heat Shield Impact Attenuation System 1967 16mm., Silent, Color 155ft., 4.25min. Whirling Membrane Solar Concentrator, Ten Foot Diameter 1964 16mm, Silent, Black & White, 95ft., 2.5min. Wind Tunnel Free Fight Investigation of a Model of a Spin Resistant Fighter Configuration 1974 16mm, Silent, Color, 9.5min. Wind Tunnel Investigation at Low Speeds of Flight Characteristics of a Sweptback-Wing Jet Transport Airplane Model Equipped with an External Flow Jet Augmented Slotted Flap 1958 16mm, Silent, Color, 250ft., 7Min. Wind Tunnel Investigation of a Balloon as Decelerator at Mach Numbers from 1.47 to 2.50 1961 Originally recorded in 16mm, Silent, Black & White, 190ft., 5.16min. Wind Tunnel Investigation of a Simulated Helicopter Engine Exhaust Interacting With Windstream 1973 16mm, Silent, Black & White, 25min. Wind Tunnel Investigation of Low-Subsonic Flight Characteristics of a Model of a Canard Airplane Designed for Supersonic Cruise 1958 16mm, Silent, Black & White Wind Tunnel Investigation of Paraglider Models at Supersonic Speeds 1961 Originally recorded in 16mm, Silent, Black & White, 177ft., 4min. Wind Tunnel Investigation of Rotor Behavior Under Extreme Operating Conditions with a Description of Blade Oscillations Attributed to Pitch-Leg Coupling 1958 16mm, Silent, Black & White, 155ft., 4.5min. A wind-tunnel investigation was made to study the behavior of a model helicopter rotor under extreme operating conditions. A 1/8-scale model of the front rotor of a tandem helicopter was built and tested to obtaining blade motion and rotor aerodynamic characteristics for conditions that could be encountered in high-speed pullout maneuvers. The data are presented without analysis. A description is given in an appendix of blade oscillations that were experienced during the course of the investigation and of the part that blade pitch-lag coupling played in contributing to the oscillatory condition. Wind Tunnel Investigation of the Aerodynamic and Structural Deflection Characteristics of an Inflatable Airplane. 1961 16mm, Silent, Color, 1200ft., 33.5min. Wind Tunnel Investigation of the Flight Characteristics of a Model of an Aspect Ration-6 Conical Parawing Utility Vehicle 1966 16mm, Silent, Color, 250ft., 7min. Wind Tunnel Tests of Opening Characteristics of Various Baseball-Type Hemispherical Parachute Demonstration 1948 16mm, Silent, Black & White Opening characteristics tests of various Baseball type hemispherical parachutes were made in the 7x10-foot tunnel. Types D-385, 389, 390, 391, 392, 393, and 394 of diameters 12 in. and 30 in. were opened in the tunnel at airspeed of 200 MPH. Type D-358 opened to a pear shape and retained this shape as airspeed was reduced to zero. Type D-389 opened only partially and the canopy started tearing. Type D-391 did not open and the canopy started tearing. These three parachutes had floating hemlines, but the rest had tacked hemlines. Type D-392 opened completely except that loops were slightly extended. Types 3-393 and D-390 did not open and the canopies started tearing, but as the airspeed was lowered, the parachutes tended to open a little. Type D-394 was opened to a slight pear shape and as the airspeed decreased, the parachute opened a little more. Results of the tests indicate that good openings require: long shroud lines, tacked hemlines, and low-porosity lower panel. The porosities of the lower panels varied from 96-318. Wind-Load Test on Sarah Antenna in Preflight Jet 1956 16mm, Silent, Black & White, 354ft, 15min. Wind-Tunnel Studies of Several Pressure Probes on a TND-8104 Nose Section 1960 16mm, Silent, Black & White, 1878ft., 52min. Wing 2, Northrop Hawk Missile (Load Condition 6; 10 Seconds After Launch; Elevated Temperature Test) 1956 16mm, Silent, Black & White Wing 7, Northrop Hawk Missile (Load Condition 4; Room Temperature) 1956 16mm, Silent, Black & White Wing 7, Northrop Hawk Missile (Load Condition 4; Room Temperature, Reinforced Room) 1956 16mm, Silent, Black & White Wing 7, Northrop Hawk Missile (Load Condition 6; Room Temperature) 1956 16mm, Silent, Black & White Wing 8, Northrop Hawk Missile (Condition 4, Room Temperature) 1956 16mm, Silent, Black & White Wing 8, Northrop Hawk Missile (Condition 6; Room Temperature) 1956 16mm, Silent, Black & White Wing Buckling Sequences on the Goodyear Inflatoplane in the Langley Full-Scale Tunnel. First Series Tests 1957 16mm, Silent, Color, 230ft., 6.5min. Wing Buckling Sequences on the Goodyear Inflatoplane in the Langley Full-Scale Tunnel--Second Series Tests 1957 16mm, Silent, Black & White, 170ft., 5min. Wing Buckling Sequences on the Goodyear Inflatoplane in the Langley Full-Scale Wind Tunnel 1957 16mm, Silent, Black & White, 290ft., 8min. Wing Root Inlet Configuration 16mm, Silent, Black & White Work Print, San Marco 16mm, Silent, Black & White Wright Lecture Film #1 16mm Presents tests made in the Gust and Free-Flight Tunnels at LAL showing some modern methods of research in the problems of flight. Wright Lecture Film #2 (High Speed Air Flow for Airfoils) 16mm Presents Schlieren photographs of high speed air flow over airfoils at various angles of attack in the rectangular high-speed tunnel. Tests covered Mach numbers ranging from 0.30 to 0.80 at angles of attack ranging from 3-Degrees to 6-Degrees. WS-107A Panel Flutter, Stage I Between Tanks Area-- Conducted in NACA Langley 9- by 18-Inch Supersonic Blowdown Flutter Tunnel During Period January 7- March 15, 1958 1958 16mm, Silent, Black & White WS-107A-2 Model in the 16-Foot Transonic Tunnel 1957 16mm, Silent, Color, 325ft., 9min. WS-107A-2 Model in the 16-Foot Transonic Tunnel 16mm, Silent, Color, 185ft., 5min. X-15 Drop Test From B-5 .049 Scale Preliminary 1958 16mm, Silent, Black & White X-15 Drop Test from B-52 .049-Scale Preliminary; 1958 16mm, Silent, Black & White X-15 Gear Shimmy Tests 1958 16mm, Silent, Black & White, 335ft., 9.25min. X-15 Jet Exhaust Study 1958 16mm, Silent, Black & White X-15 Nose Gear Shimmy Tests 1958 16mm, Silent, Black & White, 465ft., 13min. X259 Destruct Test/ X259 Gas Burst Test 16mm, Silent, Black & White XB-136-OB Nacelle Model 19 1945 16mm, Silent, Black & White Stall studies were made by means of tufts in the pressure, low-turbulence tunnel on a 1/4 scale model of the outboard nacelle of the B-36 airplane at RN of 1.68x10 [6th power] over a lift coefficient range from 0.49 to 0.043. Rear and front top views and rear and front bottom views are shown for angle of attack continuously increasing from lift coefficient of 0.409 to stall. XB-2 Spin 1940 16mm Spin and recovery tests were made in the free-spinning tunnel at the Lockheed B-2 airplane. XB-36 Air Foil Stall Progressions 16mm, Silent, Black & White Stall Progression tests were made in the 19 ft. pressure tunnel on tow wings incorporating NACA 651-210 airfoil sections, one having 0-degrees and the other 2-degrees washout. tests were run with and without a representative fuselage, and simulated contour aileron and beveled-edge aileron, in order to determine the effects of these modifications on the characteristics of the wings. The stall progressions for various configurations are presented for a Reynolds No. and a Mach no. of 4,400,000 and 0.17, respectively; with flaps neutral, partial-span flaps deflected 60-degrees, and full-span flaps deflected 60-degrees; over an angle of attack range from 5.1-degrees to 16.9-degrees and a lift coefficient range from 0.81 to 1.87. The wings had a taper ratio of 2.5 and aspect ratio of 9. XB-36 Partial Span Model 19' P.T. 16mm, Silent, Black & White Stall studies were made in the 19 ft. pressure tunnel as part of an investigation of the 4/29-scale partial-span model of the Consolidated-Vultee XB-36 airplane wing. The tests were conducted at a Reynolds No. of approximately 8,9000,000; a Mach number of approximately 0.18; single-slotted flap deflections of 0-degrees, 20-degrees, 30-degrees, 40-degrees, and 50-degrees; with midchord slots open and closed; over an angle of attack range from -2.4-degrees to 19.7-degrees; and a lift coefficient range from 0.42 to 2.22. XB-36 Stall Studies 16mm, Silent, Black & White Stall Studies were made, by means of tufts, as part of the investigation of the 4/29-scale partial-span model of the consolidated XB-36 airplane wing in the 19 ft. pressure tunnel. Motion pictures were made of the stalling characteristics of the wing with spoiler-guide aileron lateral control system. The tests were conducted at a Reynolds Number of approximately 8,900,000; a Mach number of approximately 0.18; with flaps neutral and deflected 20-degrees and 50-degrees; with vents closed and 2% vent open; over an angle of attack range from 0.2-degrees to 21.4-degrees; and a lift coefficient range from 0.17 to 2.36. XB-36 Tufts LTT Part 1 16mm XB-42 Tuft Studies 16mm, Silent, Black & White XF-104 Progress Report 1962 16mm, Sound, Color, 500ft., 14min. XF-12 Model 19' P.T. 1945 16mm, Silent, Black & White XF4F-3 Smoke flow F.S.T. 16mm, Silent, Black & White XF5V-1 Tuft Studies 16mm, Silent, Black & White Tuft studies were made by means of tufts on the 1/3-scale model of the Chance Vought XF5U-1 airplane in the full-scale tunnel. Tests were made at a tunnel airspeed of 87 MPH; over an angle of attack range from 23.2-degree to 41.2-degrees; a lift coefficient range from 0.81 to 1.12; with all surfaces neutral and propellers removed. The complete model configuration was tested with canopy open and closed and with engine nacelle and canopy fillets and with long spinners. The model with the engine nacelles only with the long spinners was also tested. The CL [max] was approximately the same with the canopy open and closed and the engine nacelle and canopy fillets had little effect on it. There was in increase, however in the CL [max] due to the long spinners. XFG-1 Tow Tests Mod #61 FFT. 1945 16mm, Silent, Black & White Tow tests were made to determine stability of a 1/17.8 scale model of the XFG-1 glider in the free-flight tunnel at the request of the Army Air Force Air Technical Service Command, Wright Field. The model was ballasted to simulate a gross weight of 5100 lb. at 15,00 ft. with the C.G. at 15% MAC. Trifurcated tow arrangement used with a four span towline. Through speed range with spoilers off model appears fairly stable at times, unstable at others; with spoilers on it is very steady laterally but a gradually worsening pitching oscillation becomes apparent at higher speeds. At a velocity of 68 MPH, with spoilers retracted, lateral stability unsatisfactory; but with spoilers deflected, lateral and longitudinal stability are satisfactory. The speed range is from 40 to 95 MPH and the flight path is 5-degree climb. XJL-1 Model 208 Rough Water 1946 16mm, Silent, Black & White Rough water landing tests were made in Tank #1 on a 1/15.5-scale model of the Columbia XJL-1 amphibian, NACA model 208M, at full-scale gross weight of 13,000 lb.; with C.G. at 28% MAC; flaps deflection 45-degrees; and at 1/2 power and landing deceleration of 3 ft./sec [2nd power]. Landings were made in waves from 2 to 6.5 ft. high and from 110 to 220 ft. long; at trim angles ranging from 6-degrees to 16.1-degrees; with maximum vertical acceleration ranging from 6-15.5 g and maximum angular acceleration ranging from 13-29 radians/sec [2nd power]. Failure of the horizontal tail occurred during the landing at 10.8-degrees trim and the propeller was damaged in the landing at 12-degrees trim. The model is shown in waves 8 ft. high and 150 ft. long at zero forward velocity. XP4M-1 Tank No.2, Part 1 16mm, Silent, Black & White XP4M-1 Tank No. 2, Part 1 16mm, Silent, Black & White XP4M-1 Tank No. 2, Part 1 16mm, Silent, Black & White XP4M-1 Tank No. 2, Part 1 16mm, Silent, Black & White XP4M-1 Tank No. 2, Part 1 16mm, Silent, Black & White XP-51 Stall Studies 16mm, Silent, Color Dive tests of XP-51 in flight were made for the purpose of obtaining fundamental data on the aerodynamic loads at high speed. The pictures show the location of the compression shock on the upper surface of the wing, the turbulent behavior of the flow behind the shock and resulting vibration of the airplane at the higher values of Mach number. These phenomena are correlated with pressure distribution and drag measurements made during the tests. Dives were made to mach numbers of 0.73, 0.78, and 0.80 with acceleration in the pull-out at 5.0g, 5.1g, and 5.3g, respectively. The vibration, resulting from the turbulent wing wake striking the tail at the highest Mach number and acceleration, was severe. No faster dives were attempted for the reason. The pressure diagrams for the upper surface of the wing show the location of minimum pressure & of the shock at 3 stages of the dive and pull-out. Instruments shown in the picture include altimeter, Mach number meter, and dive-angle indicator. Wing tufts disclosed change in flow conditions behind the shock. The total drag of the airplane as well as the profile drag on one section of the wing was measured in the dives. XS-1 Airplane 16mm XS-1 Nsg 16mm, Silent, Black & White XS-1 Transonic Research Airplane 16mm, Sound XTB2D-119' P.T. Tufts 16mm, Silent, Black & White Yawed Landing Tests Y2-2 16mm YF-100A Model Tests in the 16-Foot Transonic Tunnel. Flow on the Surface of the Wing. Ink-Flow Visualization Method. (Slats Closed and Slats Open) 1957 16mm, Silent, Black & White, 185ft., 5min. YF-12 Cold Wall Slow Off 16mm, Silent, Color YF-12 Coldwall 16mm, Silent, Color YP-80 A Flutter 1946 16mm, Silent, Black & White Transonic flutter tests were made in the 16 ft. high-speed tunnel at the Ames Aeronautical Laboratory on a partial-span wing of the Lockheed YP-80A in an attempt to eliminate the flutter. Shadowgraphs were taken at approximately 0.81 Mach number and zero lift in order to visualize the shock waves. In each case the aileron was restrained until the desired Mach number was attained and after a short flutter the aileron was again restrained. Aileron flutter with control cables loose was shown. Shadowgraphs for the standard wing and aileron showed that when the aileron fluttered the shock waves followed its motion with approximately 45-degrees lag. The flutter is believed to be the result of coupling between the aileron and shock motion through the change in separation associated with shock. Various modifications to the wing and aileron, as: spoilers on upper and lower surfaces at 50%-chord; bulges on upper and lower surfaces at 50% and 70%-chord; addition to the upper surface so as to taper the wing thickness from 15% of the chord at the tunnel wall to 13% at the tip; holes in the upper only, and in upper and lower wing surface 3 in. forward of aileron hinge; change in aileron contour so as to have flat sides with an included angle of 12-degrees; were all tested. None of the aerodynamic means which have been tried to date were successful in preventing the flutter. A small amount of damping prevented flutter at the highest Mach number attained in the wind tunnel, 0.825. Zero G: No. 6 Phase 1 16mm, Silent, Black & White, 2.5min.
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