Dryden Technical Report Server
From NTRS: Locate an electronic (PDF) copy of the document.
- LAUNCH CHARACTERISTICS OF THE X-15 RESEARCH AIRPLANE AS DETERMINED IN FLIGHT , Technical Note
Authors: Gene J. Matranga
Report Number: NASA-TN-D-723
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The first 16 air launches of the X-15 airplane demonstrated the feasibility of air launch from an asymmetric position under the wing of the B-52 carrier airplane. Use of the stability augmentation system markedly reduced the launch transients. Reasonable agreement exists between flight and predicted data.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: February 1961
- LANDING-GEAR BEHAVIOR DURING TOUCHDOWN AND RUNOUT FOR 17 LANDINGS OF THE X-15 RESEARCH AIRPLANE , Technical Memorandum
Authors: J. M. McKay and B. J. Scott
Report Number: NASA-TM-X-518
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Data are presented for the pretouchdown conditions, the impact period, and the runout phase of the landing for vertical velocities up to 9.5 feet per second and true ground speeds between 145 knots and 238 knots. The dynamic response of the airplane during the impact period is presented in the form of time histories of shock strut force and displacement, main-gear and nose-gear drag forces, upper-mass acceleration, horizontal-tail setting, horizontal-tail load, airplane angle of attack, and pitching velocity. Also included is the variation of the coefficient of friction of the main-gear skid with ground speed during the runout of a typical landing.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1961
No. Pages: 54
Keywords: Landing gear; Touchdown; X-15 aircraft.
- SKIN AND STRUCTURAL TEMPERATURES MEASURED ON THE X-15 AIRPLANE DURING A FLIGHT TO A MACH NUMBER OF 3.3 , Technical Memorandum
Authors: Robert D. Reed and Joe D. Watts
Report Number: NASA-TM-X-468
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A survey of skin and structural temperatures was obtained on the X-15 airplane during a flight to a Mach number of 3.3. Fuselage, wing, horizontal-tail, and vertical-tail temperatures are presented to show temperature variations on the external surfaces and temperature differences between the skin and internal structure. The maximum temperature recorded was 440 •F on an unsupported skin area on the lower vertical tail. Temperature differences of 400 •F were recorded between the external skin and internal spar webs on the wing. Local external temperature differences caused by the heat-sink effect of the supporting structure were as great as 220 •F. Temperature indicating paint aided in identifying the location of areas of concentrated heating on the lower surface of the wing.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 24
Keywords: Aircraft structures; Fuselages; Heating; High speed; Mach number.
- CONTROLLABILITY OF THE X-15 RESEARCH AIRPLANE WITH INTERIM ENGINES DURING HIGH-ALTITUDE FLIGHTS , Technical Memorandum
Authors: Euclid C. Holleman and Donald Reisert
Report Number: NASA-TM-X-514
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A peak geometric altitude of 136,500 feet with a minimum dynamic pressure of 10.6 lb/sq. ft. was attained with only the aerodynamic controls available to the pilot for controlling and stabilizing the airplane. Aerodynamic control was adequate throughout the flight, but at minimum dynamic pressure the airplane was lightly damped, which made precise control difficult. Because of the transient nature of the trajectory and the negligible load factors associated with the airplane oscillation, the pilot did not object to the poor dynamic characteristics of the airplane under these conditions and could satisfactory control the airplane along the trajectory.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: March 1961
Keywords: Aircraft engines; Controllability; High altitude; X-15 aircraft.
- PRELIMINARY BASE PRESSURES OBTAINED FROM THE X-15 AIRPLANE AT MACH NUMBERS FROM 1.1 TO 3.2 , Technical Note
Authors: Edwin J. Saltzman
Report Number: NASA-TN-D-1056
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Base pressure measurements have been made on the fuselage, 10 deg.-wedge vertical fin, and side fairing of the X-15 airplane. Data are presented for Mach numbers between 1.1 and 3.2 for both powered and unpowered flight. Comparisons are made with data from small-scale-model tests, semiempirical estimates, and theory. The results of this preliminary study show that operation of the interim rocket engines (propellant flow rate approximately 70 lb/sec) reduces the base drag of the X-15 by 25 to 35 percent throughout the test Mach number range. Values of base drag coefficient for the side fairing and fuselage obtained from X-15 wind-tunnel models were adequate for predicting the overall full-scale performance of the test airplane. The leading-edge sweep of the upper movable vertical fin was not an important factor affecting the fin base pressure. The power-off base pressure coefficients of the upper movable vertical fin (a 10 deg. wedge with
chord-to-thickness ratio of 5.5 and semispan-to-thickness ratio of 3.2) are in general agreement with the small-scale blunt-trailing-edge-wing data of several investigators and with two-dimensional theory.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 02
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: August 1961
No. Pages: 28
Keywords: Aerodynamic coefficients; Base pressure; Pressure measurement; Pressure ratio; X-15 aircraft.
- STATUS OF X-15 AERODYNAMIC-HEATING STUDIES
Authors: R. D. Banner and M. R. Kinsler
Report Number: H-219
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: One of the primary purposes of the X-15 program is to obtain full-scale aerodynamic-heating information that can be used to establish the adequacy of current theoretical methods and model tests. In conjunction with this purpose, a special flight was performed which maximized the heating rates and minimized the transient flight conditions. This flight reached a Mach number of 3.1. Results indicated a reasonable agreement between measured heat transfer data and simple theoretical predictions. Boundary-layer-transition data were obtained which pointed out a continuing problem of prediction that should probably be treated with conservatism until more detailed information is obtained.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
Keywords: Adiabatic conditions; Aerodynamic heating; Angle of attack; Boundary layer transition; Flight tests.
Notes: ARS Paper 1629-61
- ANALYSIS OF X-15 LANDING APPROACH AND FLARE CHARACTERISTICS DETERMINED FROM THE FIRST 30 FLIGHTS , Technical Note
Authors: Gene J. Matranga
Report Number: NASA-TN-D-1057
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The approach and flare maneuvers for the first 30 flights of the X-15 airplane and the various control problems encountered are discussed. The results afford a relatively good cross section of landing conditions that might be experienced with future glide vehicles having low lift-drag ratios. Flight-derived drag data show that preflight predictions based on wind-tunnel tests were, in general, somewhat higher than the values measured in flight. Depending on configuration, the peak lift-drag ratios from flight varied from 3.5 to 4.5 as compared with a predicted range of from 3.0 to 4.2. By employing overhead, spiral-type patterns beginning at altitudes as high as 40,000 feet, the pilots were consistently able to touch down within about +/-1,000 feet of a designated point. A typical flare was initiated at a "comfortable" altitude of about 800 feet and an indicated airspeed of approximately 300 knots., which allowed a margin of excess speed. The flap
and gear were extended when the flare was essentially completed, and an average touchdown was accomplished at a speed of about 185 knots indicated airspeed, an angle of attack of about 7 deg, and a rate of descent of about 4 feet per second. In general, the approach and landing characteristics were predicted with good accuracy in extensive preflight simulations. F-104 airplanes which simulated the X-15 landing characteristics were particularly valuable for pilot training.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: July 1961
No. Pages: 54
Keywords: Aerodynamic characteristics; Angle of attack; Approach; Descent; Drag ratio.
- REVIEW OF FLIGHT MEASUREMENTS OF SONIC BOOMS AND EFFECTS OF SHOCK WAVES ON OTHER AIRCRAFT , Conference Paper
Authors: G. H. Jordan, N. J. McLeod and B. M. Ryan
Report Number: H-230
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
Keywords: In-flight monitoring; Jordan; Measuring instruments; Shock waves; Sonic booms.
Notes: Presented at 5th Annual Symposium of the Society of Experimental Test Pilots, Beverly Hills, California, September 29–30, 1961.
- PRELIMINARY RESULTS OF AERODYNAMIC HEATING STUDIES ON THE X-15
Authors: R. D. Banner, A. E. Kuhl and R. D. Quinn
Report Number: H-234
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The results of the preliminary flight heat-transfer studies on the X-l5 airplane are presented, together with a discussion of the manner in which the data have been obtained, a comparison of measured and calculated turbulent heat-transfer coefficients, a correlation of the model test results and the flight results for turbulent heat transfer; some information on boundary-layer transition, and a comparison of measured and calculated skin temperatures at several locations on the airplane.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 18
Keywords: Aerodynamic heating; Flight tests; Supersonic flight; Turbulent heat transfer; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- STRUCTURAL HEATING EXPERIENCES OF THE X-15
Authors: A. L. Dawdy, E. E. Kordes and R. D. Reed
Report Number: H-235
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The expected structural temperatures and their effect on the development and design of the X-l5 airplane structure have been described in previous conferences, and Banner, Kuhl, and Quinn (paper no. 2) have discussed in detail the many factors affecting the heat input to the structure. The purpose of the present paper is to show the magnitude of structural temperatures measured during the flight program and to describe structural problems that have developed due to structural heating.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 15
Keywords: Aircraft structures; Temperature distribution; Temperature measurement; Thermocouples; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- BIOASTRONAUTICS SUPPORT OF THE X-15 PROGRAM
Authors: G. P. Layton, Jr., R. N. Richardson and B. Rowen
Report Number: H-242
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The techniques of air-to-ground telemetry have been used in research aircraft testing since the start of the X-l program in l946. It became apparent during the development of the X-type research aircraft that personnel responsible for aerospace medical support of the pilot were not taking full advantage of the progress in telemetry systems to monitor for medical purposes the pilot and his environment during flight. One of the research objectives of the X-l5 program is to obtain the pilot’s physiological response to flight at increased speed and altitude. This objective is accomplished with the pilot wearing a full pressure suit; therefore, this garment and biomedical data acquisition equipment, techniques, and results are discussed in this paper.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 52
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 10
Keywords: Bioastronautics; Biotelemetry; Human factors engineering; Pressure suits; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- LANDING LOADS AN DYNAMICS OF THE X-15 AIRPLANE
Authors: E. E. Kordes and J. M. McKay
Report Number: H-245
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Because the landing-gear configuration represents a marked departure from previously used configurations, the present paper has been prepared to report on the landing loads experience of the X-15 A further purpose of this paper is to review the dynamics of landing and to present results of a recent theoretical study of the effects of various parameters on the landing loads.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 11
Keywords: Aircraft landing; Landing gear; Landing loads; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- X-15 MISSION PLANNING AND OPERATIONAL PROCEDURES
Authors: R. E. Day and R. G. Hoey
Report Number: H-247
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The philosophy of the X-l5 flight-test program thus far has been to expand the flight envelope to the maximum speed and design altitude as rapidly as practical and simultaneously to obtain as much detailed research data on the hypersonic environment as possible. The envelope expansion program has been performed on an incremental performance basis; that is, each successive flight is designed to go to a slightly higher speed or altitude than the previous flight, thus permitting a reasonable extrapolation of flight-test data from one flight to the next and also building a backlog of pilot experience. The mission planning and operational procedures associated with the program are discussed in this paper. The effect on flight planning of systems reliability, stability limitations, and ranging considerations are also discussed. General piloting techniques and pilot training are mentioned.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 16
Keywords: Flight tests; Mission planning; Pilot training; Supersonic flight; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- FLIGHT CHARACTERISTICS OF X-15 HYPERSONICFLOW-DIRECTION SENSOR
Authors: J. L. Ball and W. D. Mace
Report Number: H-260
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The purpose of this paper is to discuss the experience that has been obtained through the use of the nulling ball-nose flow direction sensor during flight testing of the airplane.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 6
Keywords: Flow direction indicators; Hypersonic flight; Hypersonic flow; Servomechanisms; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- XLR99 ENGINE OPERATING EXPERIENCE
Authors: D. R. Bellman, N. E. DeMar and R. G. Leiby
Report Number: H-266
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: XLR99-RM-1 rocket engine, which was developed specifically for the X-15 airplane, is the largest rocket engine designed from the outset for use in a manned vehicle to be completely controlled by the crew. In order to provide the desired safety and controllability required by the X-15 mission, many unique features were included in the design. Delays in the development of the engine required that the initial X-15 flights be made with an interim engine. However, the first flight with the XLR99 was made in November 1960, and the engine has been used in government flight operations since February 1961. Since the first flight, fifteen flights have been made with the XLR99. This paper summarizes the XLR99 operating experience during the flight program.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 12
Keywords: Failure analysis; Flight tests; Propulsion system performance.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. ON THE X-15.
- OPERATIONAL RELIABILITY EXPERIENCES WITH THE X-15AIRCRAFT
Authors: J. E. Love and J. R. Palmer
Report Number: H-267
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: It is the purpose of this paper to describe a comprehensive picture of X-l5 operational reliability. The curves and text presented are based on actual parts failure records, flight logs, and the daily repair work sheets. It is therefore not only a picture of the reliability with regard to safety in flight, but also in view of ground preparation time and cost. Repeated system and component failures have resulted in many costly delays.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 11
Keywords: Contamination; Human performance; Low temperature environments; Reliability; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ.
- X-15 STABILITY AUGMENTATION SYSTEM
Authors: G. B. Merrick and L. W. Taylor, Jr.
Report Number: H-271
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper describes the basic damper system currently installed in the X-l5, discusses some of the problems encountered during its development and flight testing, and reviews briefly the system reliability.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 12
Keywords: Aircraft stability; Dampers; Flight tests; Reentry; X-15 aircraft.
Notes: Rewrite of 240.
- A PILOT'S IMPRESSION OF THE X-15 PROGRAM
Authors: J. A. Walker
Report Number: H-272
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: It is the intent of this paper to be critical of the X-15 because of its deficiencies or problems. It should rather be kept in mind that many compromises had to be accepted in the design of the X-15 to get on the job, and rightly so, because there are some questions which still have not been resolved.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 05
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 10
Keywords: Pilot performance; Pilot training; Test pilots; X-15 aircraft.
Notes: RES.-AIRPLANE-COMM. REPT. ON CONF. ON THE PROGR. OF THE X-15 PROJ. Replaces H-257.
- A COMPARISON OF FULL-SCALE X-15 LIFT AND DRAGCHARACTERISTICS WITH WIND-TUNNEL RESULTS AND THEORY
Authors: D. E. Fetterman, Jr., E. J. Hopkins and E. J. Saltzman
Report Number: H-274
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Data on the lift and drag characteristics of the X-15 airplane obtained in flight are shown to be in agreement with wind-tunnel-model data for Mach numbers up to 5. Existing theoretical methods are indicated to be adequate for estimating the X-l5 minimum drag but underestimated the drag due to lift and overestimated the maximum lift-drag ratio. Two-dimensional theory is shown to be adequate for predicting the base pressures behind surfaces having very blunt trailing edges) such as those on the vertical tail of the X-l5.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
Availability:
From NTRS: Locate an electronic (PDF) copy of the document.
Report Date: January 1961
No. Pages: 16
Keywords: Aerodynamic drag; Lift; Supersonic flight; X-15 aircraft.
Notes: Replaces H-259.
|
