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  1. RECENT WAKE TURBULENCE FLIGHT TEST PROGRAMS , Conference Paper
    Authors: M. R. Barber and J. J. Tymczyszyn
    Report Number: H-0001
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: In early flight tests the size and intensity of the wake vortexes generated by aircraft ranging in size from the Learjet to the C-5A and the B-747 were studied to determine the effects of aircraft configuration, weight, and speed. Early problems were related to vortex marking, the measurement of separation distance, and test techniques. Recent tests conducted with B-747 showed that vortexes were alleviated by reducing the deflection of the outboard flaps. It was found that a more rapid dissipation of the vortex system can be obtained through alterations in the span lift distribution.
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    Report Date: January 1974
    No. Pages: 17
    Keywords:      Aircraft configurations; Flight tests; Transport aircraft; Turbulent wakes; Vortices.
    Notes: Society of Experimental Test Pilots, Technical Review, vol. 12, no. 2, 1974, p. 52-68.


  2. HL-10 LIFTING BODY FLIGHT CONTROL SYSTEM CHARACTERISTICS AND OPERATIONAL EXPERIENCE , Technical Memorandum
    Authors: W. D. Painter and G. J. Sitterle
    Report Number: NASA-TM-X-2956
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A flight evaluation was made of the mechanical hydraulic flight control system and the electrohydraulic stability augmentation system installed in the HL-10 lifting body research vehicle. Flight tests performed in the speed range from landing to a Mach number of 1.86 and the altitude range from 697 meters (2300 feet) to 27,550 meters (90,300 feet) were supplemented by ground tests to identify and correct structural resonance and limit-cycle problems. Severe limit-cycle and control sensitivity problems were encountered during the first flight. Stability augmentation system structural resonance electronic filters were modified to correct the limit-cycle problem. Several changes were made to control stick gearing to solve the control sensitivity problem. Satisfactory controllability was achieved by using a nonlinear system. A limit-cycle problem due to hydraulic fluid contamination was encountered during the first powered flight, but the problem did not recur after preflight operations were improved.
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    Report Date: January 1974
    No. Pages: 36
    Keywords:      Flight control; Flight tests; HL-10 reentry vehicle; Hydraulic equipment; Transonic speed.


  3. FLIGHT-TEST INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS AND FLOW INTERFERENCE EFFECTS ABOUT THE AFT FUSELAGE OF THE F-111A AIRPLANE , Technical Note
    Authors: N. V. Taillon
    Report Number: NASA-TN-D-7563
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Static pressure measurements were made on the aft fuselage of an F-111A airplane to determine local flow characteristics and engine/airframe interaction effects. Data were obtained over the Mach number range from 0.5 to 2.0. Aspiration effects associated with low ejector nozzle expansion ratios reduced the local pressure coefficients particularly on the interfairing but also extending to the trailing edge of the nacelle. The presence of afterbodies also affected the behavior of the air flowing into and about the ejector nozzle. Pressures about the aft fuselage were improved by an increase in primary nozzle area at a supersonic speed. A comparison of wind-tunnel and flight-test results showed generally good agreement, although there was a large disparity in pressure level about the ejector nozzle. However, the shape of the data curves and the local flow behavior were basically similar.
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    Report Date: February 1974
    No. Pages: 79
    Keywords:      Aerodynamic drag; F-111 aircraft; Flow characteristics; Flow distortion; Interference drag.


  4. RESEARCH INSTRUMENTATION REQUIREMENTS FOR FLIGHT/WIND-TUNNEL TESTS OF THE YF-12 PROPULSION SYSTEM ANDRELATED FLIGHT EXPERIENCE , Conference Paper
    Authors: W. G. Schweikhard and E. J. Montoya
    Report Number: H-719
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Description of the requirements for a comprehensive flight and wind-tunnel propulsion research program to examine the predictability of inlet performance, evaluate the effects of high-frequency pressure phenomena on inlets, and investigate improved control concepts in order to cope with airframe interactions. This program is unique in that it requires precise similarity of the geometry of the flight vehicle and tunnel modes; the test conditions, including local flow at the inlet; and instrumentation. Although few wind-tunnel instrumentation problems exist, many problems emerge during flight tests because of the thermal environment. Mach 3 flight temperatures create unique problems with transducers, connectors, and wires. All must be capable of withstanding continuous 1000 F temperatures, as well as the mechanical stresses imposed by vibration and thermal cycling.
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    Report Date: January 1974
    No. Pages: 21
    Keywords:      Data acquisition; Flight tests; Flow measurement; Propulsion system performance; Supersonic aircraft.
    Notes: In: Instrumentation for airbreathing propulsion; Proceedings of the Symposium, Monterey, Calif., September 19-21, 1972.


  5. INSTRUMENTATION FOR IN-FLIGHT DETERMINATION OF STEADY-STATE AND DYNAMIC INLET PERFORMANCE IN SUPERSONIC AIRCRAFT , Conference Paper
    Authors: R. H. Smith and F. W. Burcham, Jr.
    Report Number: H-720
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: No abstract available.
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    Report Date: January 1974
    No. Pages: 18
    Keywords:      Aircraft performance; Flight tests; In-flight monitoring; Measuring instruments; Propulsion system performance.
    Notes: In: Instrumentation for airbreathing propulsion; Proceedings of the Symposium, Monterey, Calif., September 19-21, 1972. Cambridge, Mass., MIT Press, 1974, p. 41-58.


  6. FLIGHT EVALUATION OF HL-10 LIFTING BODY HANDLING QUALITIES AT MACH NUMBERS FROM 0.30 TO 1.86 , Technical Note
    Authors: R. W. Kempel and J. A. Manke
    Report Number: NASA-TN-D-7537
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The longitudinal and lateral-directional handling qualities of the HL-10 lifting body vehicle were evaluated in flight at Mach numbers up to 1.86 and altitudes up to approximately 27,450 meters (90,000 feet). In general, the vehicle's handling qualities were considered to be good. Approximately 91 percent of the pilot ratings were 3.5 or better, and 42.4 percent were 2.0. Handling qualities problems were encountered during the first flight due to problems with the control system and vehicle aerodynamics. Modifications of the flight vehicle corrected all deficiencies, and no other significant handling qualities problems were encountered.
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    Report Date: January 1974
    No. Pages: 48
    Keywords:      Aerodynamic configurations; Flight tests; HL-10 reentry vehicle; Lateral control; Longitudinal control.


  7. FLIGHT-DETERMINED LAG OF ANGLE-OF-ATTACK ANDANGLE-OF-SIDESLIP SENSORS IN THE YF-12A AIRPLANE FROM ANALYSIS OFDYNAMIC MANEUVERS , Technical Note
    Authors: G. B. Gilyard and D. Belte
    Report Number: NASA-TN-D-7819
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Magnitudes of lags in the pneumatic angle-of-attack and angle-of-sideslip sensor systems of the YF-12A airplane were determined for a variety of flight conditions by analyzing stability and control data. The three analysis techniques used are described. An apparent trend with Mach number for measurements from both of the differential-pressure sensors showed that the lag ranged from approximately 0.15 second at subsonic speed to 0.4 second at Mach 3. Because Mach number was closely related to altitude for the available flight data, the individual effects of Mach number and altitude on the lag could not be separated clearly. However, the results indicated the influence of factors other than simple pneumatic lag.
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    Report Date: October 1974
    No. Pages: 32
    Keywords:      Angle of attack; Fighter aircraft; Flight instruments; Instrument errors; Sideslip.


  8. FLIGHT EVALUATION OF ADVANCED CONTROL SYSTEMS AND DISPLAYS ON A GENERAL AVIATION AIRPLANE , Technical Note
    Authors: P. C. Loschke, M. R. Barber, E. K. Enevoldson and T. C. McMurtry
    Report Number: NASA-TN-D-7703
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A flight-test program was conducted to determine the effect of advanced flight control systems and displays on the handling qualities of a light twin-engined airplane. A flight-director display and an attitude-command control system, used separately and in combination, transformed a vehicle with poor handling qualities during ILS approaches in turbulent air into a vehicle with good handling qualities. The attitude-command control system also improved the ride qualities of the airplane. A rate-command control system made only small improvements to the airplane's ILS handling qualities in turbulence. Both the rate- and the attitude-command control systems reduced stall warning in the test airplane, increasing the likelihood of inadvertent stalls. The final approach to the point of flare was improved by both the rate- and the attitude-command control systems. However, the small control wheel deflections necessary to flare were unnatural and tended to cause overcontrolling during flare. Airplane handling qualities are summarized for each control-system and display configuration.
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    Report Date: June 1974
    No. Pages: 50
    Keywords:      Aircraft performance; Display devices; Flight control; Flight tests; General aviation aircraft.


  9. AN OVERVIEW OF PARAMETER ESTIMATION TECHNIQUES ANDAPPLICATIONS IN AIRCRAFT FLIGHT TESTING
    Authors: H. A. Rediess
    Report Number: H-786
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Parameter estimation is discussed as it applies to aircraft flight testing, and an overview of the symposium is presented. The evolution of techniques used in flight testing is reviewed briefly, and it is pointed out how the changing character of the aircraft tested and the availability of advanced data systems have promoted this evolution. Recent advances in optimal estimation theory have stimulated widespread interest and activity in parameter estimation. The framework of these advanced techniques is outlined to set the stage for subsequent papers. The session topics are introduced and related to the requirements of flight-test research.
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    Report Date: April 1974
    No. Pages: 18
    Keywords:      Aerodynamic characteristics; Aerodynamic coefficients; Aeronautical engineering; Flight tests; Parameterization.
    Notes: In its Parameter Estimation Tech. and Appl. in Aircraft Flight Testing p 1-18. NASA TN-D-7647.


  10. DETERMINATION OF PROPULSION-SYSTEM-INDUCED FORCES ANDMOMENTS OF A MACH 3 CRUISE AIRCRAFT
    Authors: G. B. Gilyard
    Report Number: H-787
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: During the joint NASA/USAF flight research program with the YF-12 airplane, the Dutch roll damping was found to be much less during automatic inlet operation than during fixed inlet operation at Mach numbers greater than 2.5 and with the yaw stability augmentation system off. It was concluded that the significant reduction in Dutch roll damping was due to the forces and moments induced by the variable-geometry features of the inlet. Two stability-derivative extraction techniques were applied to the flight data; the recently developed Newton-Raphson technique and the time vector method. These techniques made it possible to determine the forces and moments generated by spike and bypass door movement.
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    Report Date: April 1974
    No. Pages: 6
    Keywords:      Aerodynamic forces; Intake systems; Propulsion system performance; Reconnaissance aircraft; YF-12 aircraft.
    Notes: In its Parameter Estimation Tech. and Appl. in Aircraft Flight Testing p 369-374. NASA TN-D-7647.


  11. IDENTIFICATION OF AIRCRAFT STABILITY AND CONTROL DERIVATIVESIN THE PRESENCE OF TURBULENCE
    Authors: K. W. Iliff
    Report Number: H-788
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A maximum likelihood estimator for a linear system with state and observation noise is developed to determine stability and control derivatives from flight data obtained in the presence of turbulence. The formulation for the longitudinal short-period mode is presented briefly, including a special case that greatly simplifies the problem if the measurement noise on one signal is negligible. The effectiveness and accuracy of the technique are assessed by applying it first to simulated flight data, in which the true parameter values and state noise are known, then to actual flight data obtained in turbulence. The results are compared with data obtained in smooth air and with wind-tunnel data. The complete maximum likelihood estimator, which accounts for both state and observation noise, is shown to give the most accurate estimate of the stability and control derivatives from flight data obtained in turbulence. It is superior to the techniques that ignores state noise and to the simplified method that neglects the measurement noise on the angle-of-attack signal.
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    Report Date: April 1974
    No. Pages: 37
    Keywords:      Aircraft control; Aircraft stability; Angle of attack; Stability derivatives; Turbulence.
    Notes: In its Parameter Estimation Tech. and Appl. in Aircraft Flight Testing p 77-114. NASA TN-D-7647.


  12. FLIGHT STUDY OF A VEHICLE OPERATIONAL STATUS AND MONITORING SYSTEM , Technical Note
    Authors: J. E. Love, W. J. Fox and E. J. Wicklund
    Report Number: NASA-TN-D-7546
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: An analog onboard monitoring system was installed on a YF-12 airplane as the first phase of a program to monitor the engine inlet and portions of the airplane's electrical and fuel management subsystems in flight. The system provided data which were considered to form a suitable base for diagnostic test logic and decision criteria for the rest of the program. The data were also adequate for the purpose of maintaining the engine inlet and identifying malfunctions within it. The investigation showed that the requirements of an onboard monitoring system should be considered during the original design of the system to be monitored.
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    Report Date: January 1974
    No. Pages: 13
    Keywords:      Aircraft equipment; Analog data; Monitors; Onboard equipment; Systems analysis.


  13. A SIMPLIFIED FLIGHT-TEST METHOD FOR DETERMINING AIRCRAFT TAKEOFF PERFORMANCE THAT INCLUDES EFFECTS OF PILOT TECHNIQUE , Technical Note
    Authors: T. J. Larson and W. G. Schweikhard
    Report Number: NASA-TN-D-7603
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A method for evaluating aircraft takeoff performance from brake release to air-phase height that requires fewer tests than conventionally required is evaluated with data for the XB-70 airplane. The method defines the effects of pilot technique on takeoff performance quantitatively, including the decrease in acceleration from drag due to lift. For a given takeoff weight and throttle setting, a single takeoff provides enough data to establish a standardizing relationship for the distance from brake release to any point where velocity is appropriate to rotation. The lower rotation rates penalized takeoff performance in terms of ground roll distance; the lowest observed rotation rate required a ground roll distance that was 19 percent longer than the highest. Rotations at the minimum rate also resulted in lift-off velocities that were approximately 5 knots lower than the highest rotation rate at any given lift-off distance.
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    Report Date: February 1974
    No. Pages: 41
    Keywords:      Aircraft performance; B-70 aircraft; Flight tests; Pilot performance; Takeoff.


  14. FLIGHT INVESTIGATION OF APPROACH AND FLARE FROM SIMULATED BREAKOUT ALTITUDE OF A SUBSONIC JET TRANSPORT AND COMPARISON WITHANALYTICAL MODELS , Technical Note
    Authors: N. W. Matheny
    Report Number: NASA-TN-D-7645
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Satisfactory and optimum flare windows are defined from pilot ratings and comments. Maximum flare normal accelerations, touchdown rates of sink, and total landing maneuver time increments are summarized as a function of approach airspeed margin (with respect to reference airspeed) and flare initiation altitude. The effects of two thrust management techniques are investigated. Comparisons are made with predictions from three analytical models and the results of a simulator study. The approach speed margin was found to have a greater influence on the flare initiation altitude than the absolute airspeed. The optimum airspeed was between the reference airspeed and the reference airspeed plus 10 knots. The optimum flare initiation altitude range for unrestricted landings was from 11 meters to 20 meters (36 feet to 66 feet), and the landing time in the optimum window was 8 seconds. The duration of the landing maneuver increased with increasing flare initiation altitude and with increasing speed margins on the approach.
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    Report Date: April 1974
    No. Pages: 36
    Keywords:      Aircraft landing; Aircraft performance; Glide paths; Jet aircraft; Transport aircraft.


  15. FLIGHT-MEASURED INLET PRESSURE TRANSIENTS ACCOMPANYING ENGINE COMPRESSOR SURGES ON THE F-111A AIRPLANE , Technical Note
    Authors: J. Nugent and J. K. Holzman
    Report Number: NASA-TN-D-7696
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Two-F-111A airplanes were subjected to conditions that caused engine compressor surges and accompanying duct hammershock pressure transients. Flight speed ranged from Mach 0.71 to Mach 2.23, and altitude varied from approximately 3200 meters to 14,500 meters. A wide range of compressor pressure ratios was covered. Stabilized free-stream, engine, and duct conditions were established before each compressor surge. Dynamic pressure instrumentation at the compressor face and in the duct recorded the pressure transients associated with the surges. Hammershock pressures were analyzed with respect to the stabilized conditions preceding the compressor surges. The hammershock transients caused large pressure rises at the compressor face and in the duct. Hammershock pressure ratios at the compressor face were not affected by free-stream Mach number or altitude but were functions of engine variables, such as compressor pressure ratio. The maximum hammershock pressure ratio of approximately 1.83 occurred at a compressor pressure ratio of approximately 21.7.
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    Report Date: June 1974
    No. Pages: 30
    Keywords:      Compressors; Ducted flow; F-111 aircraft; Inlet pressure; Transient pressures.


  16. PARAMETER ESTIMATION TECHNIQUES AND APPLICATION IN AIRCRAFT FLIGHT TESTING , Technical Note
    Authors: Various
    Report Number: NASA-TN-D-7647
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Technical papers presented at the symposium by selected representatives from industry, universities, and various Air Force, Navy, and NASA installations are given. The topics covered include the newest developments in identification techniques, the most recent flight-test experience, and the projected potential for the near future.
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    Report Date: April 1974
    No. Pages: 392
    Keywords:      Aircraft control; Conferences; Flight tests; Maximum likelihood estimates; Parameterization.


  17. A DIGITAL FLY-BY-WIRE TECHNOLOGY DEVELOPMENT PROGRAM USING AN F-8C TEST AIRCRAFT , Conference Paper
    Authors: C. R. Jarvis
    Report Number: H-812
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A digital fly-by-wire flight control system has been installed in an F-8C test airplane and has undergone extensive ground and flight testing as part of an overall program to develop digital fly-by-wire technology. This is the first airplane to fly with a digital fly-by-wire system as its primary means of control and with no mechanical reversion capability. Forty-two test flights were made for a total flight time of 57 hours. Six pilots participated in the evaluation. This paper presents an overview of the digital fly-by-wire program and discusses some of the flight-test results.
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    Report Date: January 1974
    No. Pages: 11
    Keywords:      Computer programs; Digital navigation; F-8 aircraft; Flight tests; Fly by wire control.
    Notes: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 12th, Washington, D.C., Jan. 30-Feb. 1, 1974.


  18. EXPERIMENTAL DETERMINATION OF AIRPLANE MASS AND INERTIAL CHARACTERISTICS , Technical Report
    Authors: C. H. Wolowicz and R. B. Yancey
    Report Number: NASA-TR-R-433
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Current practices are evaluated for experimentally determining airplane center of gravity, moments of inertia, and products of inertia. The techniques discussed are applicable to bodies other than airplanes. In pitching- and rolling-moment-of-inertia investigations with the airplane mounted on and pivoted about knife edges, the nonlinear spring moments that occur at large amplitudes of oscillation can be eliminated by using the proper spring configuration. The single-point suspension double-pendulum technique for obtaining yawing moments of inertia, products of inertia, and the inclination of the principal axis provides accurate results from yaw-mode oscillation data, provided that the sway-mode effects are minimized by proper suspension rig design. Rocking-mode effects in the data can be isolated.
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    Report Date: October 1974
    No. Pages: 66
    Keywords:      Aircraft configurations; Center of gravity; Flight characteristics; Moments of inertia; Pitch (inclination).


  19. FLIGHT EXPERIENCE WITH THE DECELERATING NOISE ABATEMENT APPROACH , Technical Memorandum
    Authors: T. W. Putnam
    Report Number: NASA-TM-X-56020
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The noise of older aircraft can be reduced in two principal ways: retrofitting the aircraft with a quiet propulsion system, and changing the flight operational procedures used in flying the aircraft. The former approach has already proved to be expensive, time consuming, and difficult to implement even though low-noise propulsion system technology exists. The latter method seems to hold promise of being less expensive and easier to implement. One operational technique which might reduce the noise beneath the landing approach path is the decelerating approach. This technique requires intercepting the 3 deg approach path at a relatively high speed with the aircraft in the cruise configuration, then reducing the thrust to idle and allowing the aircraft to decelerate along the 3 deg approach path. As the appropriate airspeed is achieved, the landing flaps and landing gear are deployed for a normal flare and landing. Because the engines, which are the predominant noise source on landing approach, are at idle thrust, a significant reduction in the noise beneath the approach path should be realized.
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    Report Date: January 1974
    No. Pages: 18
    Keywords:      Aircraft landing; Aircraft noise; Approach control; Flight paths; Noise reduction.


  20. FLIGHT EXPERIENCE WITH A PIVOTING TRAVERSING BOUNDARY-LAYER PROBE , Technical Memorandum
    Authors: L. C. Montoya, D. A. Brauns and R. E. Cissell
    Report Number: NASA-TM-X-56022
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A pivoting traversing boundary layer probe was evaluated in flight on an F-104 airplane. The evaluation was performed at free stream Mach numbers from 0.8 to 2.0. The unit is described, and operating problems and their solutions are discussed. Conventional boundary layer profiles containing variations in flow angle within the viscous layer are shown for free stream Mach numbers of 0.8, 1.6, and 2.0. Although the unit was not optimized for size and weight, it successfully measured simultaneously flow angularity, probe height, and pitot pressure through the boundary layer.
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    Report Date: January 1974
    No. Pages: 16
    Keywords:      Atmospheric pressure; Boundary layers; F-104 aircraft; Ionospheric sounding; Pitot tubes.


  21. PRELIMINARY MEASUREMENTS OF AIRCRAFT AERODYNAMIC NOISE , Conference Paper
    Authors: P. L. Lasagna and T. W. Putnam
    Report Number: H-821
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flight measurements of aerodynamic noise were made on an AeroCommander airplane with engines off and a JetStar airplane with engines at both idle power and completely shut off. The overall sound level for these airplanes in the landing configuration varied as the sixth power of the aircraft velocity. For the JetStar airplane, the overall sound level decreased as the inverse square of the distance in the lateral direction. The aerodynamic noise was approximately 11 decibels below the FAR Part 36 noise level for the JetStar airplane. The landing gear were a significant contributor to aerodynamic noise for both aircraft.
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    Report Date: June 1974
    No. Pages: 8
    Keywords:      Acoustic measurement; Aerodynamic noise; Aircraft noise; C-140 aircraft; Flight tests.
    Notes: American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference, 7th, Palo Alto, Calif., June 17-19, 1974. AIAA Paper 74-572.


  22. INITIAL RESULTS FROM FLIGHT TESTING A LARGE, REMOTELY PILOTED AIRPLANE MODEL , Technical Memorandum
    Authors: E. C. Holleman
    Report Number: NASA-TM-X-56024
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The first four flights of a remotely piloted airplane model showed that a flight envelope can be expanded rapidly and that hazardous flight tests can be conducted safely with good results. The flights also showed that aerodynamic data can be obtained quickly and effectively over a wide range of flight conditions, clear and useful impressions of handling and controllability of configurations can be obtained, and present computer and electronic technology provide the capability to close flight control loops on the ground, thus providing a new method of design and flight test for advanced aircraft.
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    Report Date: March 1974
    No. Pages: 42
    Keywords:      Aerodynamic stalling; Aircraft performance; F-15 aircraft; Flight tests; Remotely piloted vehicles.


  23. COOPERATIVE AIRFRAME/PROPULSION CONTROL FOR SUPERSONIC CRUISE AIRCRAFT , Conference Paper
    Authors: W. G. Schweikhard and D. T. Berry
    Report Number: H-825
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Interactions between propulsion systems and flight controls have emerged as a major control problem on supersonic cruise aircraft. This paper describes the nature and causes of these interactions and the approaches to predicting and solving the problem. Integration of propulsion and flight control systems appears to be the most promising solution if the interaction effects can be adequately predicted early in the vehicle design. Significant performance, stability, and control improvements may be realized from a cooperative control system.
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    Report Date: April 1974
    No. Pages: 8
    Keywords:      Aircraft design; Airframes; Flight control; Propulsion system performance; Supersonic aircraft.
    Notes: Society of Automotive Engineers, Air Transportation Meeting, Dallas, Tex., Apr. 30-May 2, 1974.


  24. NASA FLIGHT RESEARCH CENTER SCALE F-15 REMOTELYPILOTED RESEARCH VEHICLE PROGRAM
    Authors: G. P. Layton
    Report Number: H-826
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A remotely piloted research vehicle (RPRV) program was conducted with a 3/8-scale model of an F-15 airplane to determine the usefulness of the RPRV testing technique in high risk flight testing such as spin testing. The results of the first flights of the program are presented. The program has shown that the RPRV technique, including the use of a digital control system, is a viable method for obtaining flight research data. Also presented are some negative aspects that have been learned about the RPRV technique in terms of model size, command frequency, and launch technique.
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    Report Date: January 1974
    No. Pages: 14
    Keywords:      F-15 aircraft; Flight tests; Remotely piloted vehicles; Research vehicles; Scale models.
    Notes: In Soc. of Flight Test Engr. Advan. in Flight Test Eng. .


  25. FLIGHT EVALUATION OF A MACH 3 CRUISE LONGITUDINAL AUTOPILOT , Conference Paper
    Authors: G. B. Gilyard, J. W. Smith and V. L. Falkner
    Report Number: H-829
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: At high Mach numbers (approximately 3) and altitudes greater than 70,000 feet, the original altitude and Mach hold modes of the YF-12 autopilot produced aircraft excursions that were erratic or divergent or both. Data analysis and simulator studies showed that static pressure port sensitivity to angle of attack had a detrimental effect on the performance of both altitude and Mach hold modes. Good altitude hold performance was obtained when a high-passed pitch rate feedback was added to compensate for angle-of-attack sensitivity and the altitude error and integral altitude gains were reduced. Good Mach hold performance was obtained with the removal of angle-of-attack sensitivity.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: August 1974
    No. Pages: 11
    Keywords:      Aircraft stability; Angle of attack; Automatic pilots; Cruising flight; Flight tests.
    Notes: American Institute of Aeronautics and Astronautics, Mechanics and Control of Flight Conference, Anaheim, Calif., Aug. 5-9, 1974. AIAA Paper 74-910.


  26. DRAG REDUCTION OBTAINED BY ROUNDING VERTICAL CORNERS ON A BOX-SHAPED GROUND VEHICLE , Technical Memorandum
    Authors: E. J. Saltzman and R. R. Meyer, Jr.
    Report Number: NASA-TM-X-56023
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A box-shaped ground vehicle was used to simulate the aerodynamic drag of delivery vans, trucks, and motor homes. A coast-down method was used to define the drag of this vehicle in a configuration with all square corners and a modified configuration with the four vertical corners rounded. The tests ranged in velocity from 30 miles per hour to 65 miles per hour, and Reynolds numbers ranged from 4.4 x 1,000,000 to 1.0 x 10 to the 7th power based on vehicle length. The modified configuration showed a reduction in aerodynamic drag of about 40 percent as compared to the square cornered configuration.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 02
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    Report Date: March 1974
    No. Pages: 21
    Keywords:      Aerodynamic drag; Boxes (containers); Corner flow; Drag reduction; Trucks.


  27. COMPENSATED AND UNCOMPENSATED NOSE BOOM STATIC PRESSURES MEASURED FROM TWO AIR DATA SYSTEMS ON A SUPERSONIC AIRPLANE , Technical Memorandum
    Authors: T. J. Larson
    Report Number: NASA-TM-X-3132
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Two static-pressure-measuring air data systems that were used on the YF-12 airplane for supersonic flight testing were compared. One system consisted of a nose boom pitot-static probe with two sets of static-pressure orifices designed for static-pressure error compensation, two air data computers, and a photopanel for recording. The other system consisted of an identical nose boom probe and a third set of static-pressure orifices not designed for error compensation, pressure transducers for direct pressure measurements instead of air data computers, and 5 pulse code modulation system for recording. The comparisons showed that the uncompensated static-pressure orifices provided more accurate air data measurements than either set of compensated static-pressure sources. Whereas the uncompensated static-pressure source was relatively insensitive to angle of attack, the compensated sources were characterized by a position error at supersonic speeds that increased with angle of attack and Mach number. Pitot-static measurements acquired by using air data computers that incorporate cams for static error compensation provide reference data that are less accurate than similar measurements made by pressure transducers.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 02
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    Currently this document is not available on-line.
    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: November 1974
    No. Pages: 25
    Keywords:      Air data systems; Data systems; Pressure measurement; Static pressure; YF-12 aircraft.


  28. MEASUREMENTS OF SONIC BOOMS GENERATED BY AN AIRPLANE FLYING AT MACH 3.5 AND 4.8 , Technical Memorandum
    Authors: K. S. Green and T. W. Putnam
    Report Number: NASA-TM-X-3126
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Sonic booms generated by the X-15 airplane flying at Mach numbers of 3.5 and 4.8 were measured. The experimental results agreed within 12 percent with results obtained from theoretical methods. No unusual phenomena related to overpressure were encountered. Scaled data from the X-15 airplane for Mach 4.8 agreed with data for an SR-71 airplane operating at lower Mach numbers and similar altitudes. The simple technique used to scale the data on the basis of airplane lift was satisfactory for comparing X-15 and SR-71 sonic boom signatures.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: October 1974
    No. Pages: 24
    Keywords:      Aerodynamic noise; Acoustic measurement; Sonic booms; Supersonic speed; X-15 aircraft.


  29. HIGH ALTITUDE TURBULENCE ENCOUNTERED BY THE SUPERSONIC YF-12A AIRPLANE , Conference Paper
    Authors: L. J. Ehernberger
    Report Number: H-842
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 47
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: January 1974
    No. Pages: 8
    Keywords:      Acceleration (physics); Aircraft hazards; Atmospheric turbulence; Turbulence effects; YF-12 aircraft.
    Notes: In: Conference on Aerospace and Aeronautical Meteorology, 6th, El Paso, Tex., November 12-15, 1974.


  30. USE OF A PITOT-STATIC PROBE FOR DETERMINING WING SECTION DRAG IN FLIGHT AT MACH NUMBERS FROM 0.5 TO APPROXIMATELY 1.0 , Technical Memorandum
    Authors: L. C. Montoya, M. A. Economu and R. E. Cissell
    Report Number: NASA-TM-X-56025
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The use of a pitot-static probe to determine wing section drag at speeds from Mach 0.5 to approximately 1.0 was evaluated in flight. The probe unit is described and operational problems are discussed. Typical wake profiles and wing section drag coefficients are presented. The data indicate that the pitot-static probe gave reliable results up to speeds of approximately 1.0.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 02
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    Report Date: July 1974
    No. Pages: 22
    Keywords:      Aircraft wakes; Drag measurement; Flight tests; Pitot tubes; Subsonic speed.


  31. TEST TECHNIQUES, INSTRUMENTATION, AND DATA PROCESSING
    Authors: W. G. Schweikhard
    Report Number: H-851
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Procedures for determining the effects of dynamic distortion on engine stability are analyzed. The test techniques, methods and types of instrumentation, and data processing functions are described. The advantages and limitations of various methods are reported. It is emphasized that ground facility tests are only a simulation of the flight environment, that instrumentation provides only a partial representation of the physical phenomena, and that poorly organized data processing procedures can impede and even distort the final result.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 07
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: October 1974
    No. Pages: 43
    Keywords:      Air flow; Flight simulation; Flow distortion; Gas turbine engines; Propulsion system performance.
    Notes: In AGARD Distortion Induced Eng. Instability.


  32. A DYNAMIC PRESSURE GENERATOR FOR CHECKING COMPLETE PRESSURE SENSING SYSTEMS INSTALLED ON AN AIRPLANE , Technical Memorandum
    Authors: D. M. DeMarco
    Report Number: NASA-TM-X-56026
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A portable dynamic pressure generator, how it operates, and a test setup on an airplane are described. The generator is capable of providing a sinusoidal pressure having a peak-to-peak amplitude of 3.5 N/sq cm (5 psi) at frequencies ranging from 100 hertz to 200 hertz. A typical power spectral density plot of data from actual dynamic pressure fluctuation tests within the air inlet of the YF-12 airplane is presented.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 35
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    Report Date: September 1974
    No. Pages: 12
    Keywords:      Aircraft equipment; Engine inlets; Portable equipment; Power spectra; Pressure measurement.


  33. FLIGHT-TEST TECHNIQUES FOR OBTAINING VALID COMPARISONS OF WIND-TUNNEL AND FLIGHT RESULTS FROM TESTS ON A YF-12MIXED-COMPRESSION INLET , Conference Paper
    Authors: P. J. Reukauf, W. G. Schweikhard and H. Arnaiz
    Report Number: H-865
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: No abstract available.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    Currently this document is not available on-line.
    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: October 1974
    No. Pages: 14
    Keywords:      Aircraft engines; Engine inlets; Flight tests; Propulsion system performance; Supersonic inlets.
    Notes: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 10th, San Diego, Calif., Oct. 21-23, 1974. AIAA Paper 74-1195.


  34. A REMOTELY AUGMENTED VEHICLE APPROACH TO FLIGHT TESTING RPV CONTROL SYSTEMS , Technical Memorandum
    Authors: D. A. Deets and J. W. Edwards
    Report Number: NASA-TM-X-56029
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: A remotely augmented vehicle concept for flight testing advanced control systems was developed as an outgrowth of a remotely piloted research vehicle (RPV) program in which control laws are implemented through telemetry uplink and downlink data channels using a general purpose ground based digital computer which provides the control law computations. Some advantages of this approach are that the cost of one control system facility is spread over a number of RPV programs, and control laws can be changed quickly as required, without changing the flight hardware. The remotely augmented vehicle concept is described, and flight test results from a subscale F-15 program are discussed. Suggestions of how the concept could lead to more effective testing of RPV control system concepts, and how it is applicable to a military RPV reconnaissance mission are given.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    Report Date: November 1974
    No. Pages: 26
    Keywords:      Aerial reconnaissance; Aircraft control; Automatic flight control; Flight tests; Remotely piloted vehicles.


  35. HIMAT - A NEW APPROACH TO THE DESIGN OF HIGHLY MANEUVERABLE AIRCRAFT , Conference Paper
    Authors: D. R. Bellman and D. A. Kier
    Report Number: H-873
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Needed improvements in the maneuvering performance of combat aircraft appear to be possible through the simultaneous application of advances in various disciplines in such a way that they complement one another and magnify the benefits derived. The highly maneuverable aircraft technology (HiMAT) program is being conducted to investigate such multidisciplinary concepts. The program has three phases: preliminary studies, conceptual design studies, and the final design and construction of a test airplane. Work is now in the second phase. The test airplane will be a scaled model flown by a remotely piloted research vehicle technique. This paper outlines the HiMAT program and indicates the types of concepts being considered.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: October 1974
    No. Pages: 8
    Keywords:      Aircraft control; Aircraft design; Aircraft maneuvers; Military aircraft; NASA programs.
    Notes: Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting, San Diego, Calif., Oct. 1-3, 1974. SAE Paper 740859.


  36. AERODYNAMIC DRAG REDUCTION TESTS ON A FULL-SCALE TRACTOR-TRAILER COMBINATION WITH SEVERAL ADD-ON DEVICES , Technical Memorandum
    Authors: L. C. Montoya and L. L. Steers
    Report Number: NASA-TM-X-56028
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Aerodynamic drag tests were performed on a conventional cab-over-engine tractor with a 45-foot trailer and five commercially available or potentially available add-on devices using the coast-down method. The tests ranged in velocity from approximately 30 miles per hour to 65 miles per hour and included some flow visualization. A smooth, level runway at Edwards Air Force Base was used for the tests, and deceleration measurements were taken with both accelerometers and stopwatches. An evaluation of the drag reduction results obtained with each of the five add-on devices is presented.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 02
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    Currently this document is not available on-line.
    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: December 1974
    No. Pages: 26
    Keywords:      Accelerometers; Aerodynamic drag; Drag reduction; Performance tests; Trucks.
    Notes: Presented at the Reduction of Aerodynamic Drag of Trucks Conf., Pasadena, Calif., 10-11 Oct. 1974.


  37. ATMOSPHERIC EFFECTS ON THE INLET SYSTEM OF THE YF-12 AIRCRAFT , Conference Paper
    Authors: R. H. Smith and C. A. Bauer
    Report Number: H-879
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: Flights of a YF-12 airplane were performed over a wide range of operating conditions so that detailed comparisons could be made with data from tests on scale models in NASA ground facilities. Extensive flight instrumentation for inlet performance comparisons provided flight data that also lend insight into supersonic inlet operation during atmospheric turbulence. Pressure and flow direction measurements near the inlet gave results different from conventional accelerometer data normally used for flight determination of turbulence severity. A nonturbulent atmospheric temperature excursion during an XB-70 flight caused inlet duct pressure variations as extreme as those experienced during heavy turbulence on the YF-12 airplane.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: January 1974
    No. Pages: 22
    Keywords:      Environment effects; Fighter aircraft; Research aircraft; Supersonic aircraft; Supersonic inlets.
    Notes: In: National Conference on Environmental Effects on Aircraft and Propulsion Systems, 11th, Trenton, N.J., May 21-23, 1974, Proceedings. (A74-39733 20-28) Trenton, N.J., U.S. Naval Air Propulsion Test Center, 1974.


  38. RPRVS - THE FIRST AND FUTURE FLIGHTS , Journal Article
    Authors: R. D. Reed
    Report Number: H-880
    Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
    Abstract: The merits of the RPRV (remotely piloted research vehicle) concept are discussed, along with its historical background and development culmination in the 3/8-scale F-15. The use of RPRVs is shown to be especially attractive when testing must be done at low cost, or in quick response to demand, or when hazardous testing must assure the safety of proceeding to manned vehicles.
    Distribution/Availability: Unclassified - Unlimited
    Subject Category: 05
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    From the NTRS FAQ: Where do I go for a hardcopy of the report?
    Report Date: April 1974
    No. Pages: 17
    Keywords:      Aircraft control; Automatic pilots; Flight tests; Remotely piloted vehicles; Research vehicles.
    Notes: Astronautics and Aeronautics, vol. 12, Apr. 1974, p. 26-42.
 
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