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- OPERATIONAL EXPERIENCE WITH THE X-15 REACTION CONTROL AND REACTION AUGMENTATION SYSTEMS , Technical Note
Authors: C. R. Jarvis and W. P. Lock
Report Number: NASA-TN-D-2864
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper describes the X-15 reaction control system and discusses the system characteristics, operational experiences, and development problems. Data are presented from X-15 high-altitude flights during which both the manual control and reaction augmentation systems were operated.
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Report Date: June 1965
No. Pages: 50
Keywords: Altitude; Augmentation; Dynamic pressure; High altitude; Low pressure.
- FLIGHT-MEASURED WING SURFACE PRESSURES AND LOADS FOR THE X-15 AIRPLANE AT MACH NUMBERS FROM 1.2 TO 6.0 , Technical Note
Authors: J. S. Pyle
Report Number: NASA-TN-D-2602
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Flight measurement of pressure distributions on wing and wing-body junction of X-15 aircraft.
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Report Date: January 1965
No. Pages: 45
Keywords: Body-wing configurations; Loads (forces); Mach number; Pressure; Pressure distribution.
- FLIGHT-DETERMINED LOW-SPEED LIFT AND DRAG CHARACTERISTICS OF THE LIGHTWEIGHT M2-F1 LIFTING BODY , Technical Note
Authors: V. W. Horton, R. C. Eldredge and R. E. Klein
Report Number: NASA-TN-D-3021
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The low-speed lift and drag characteristics of a manned, lightweight M-2 lifting-body vehicle were determined in unpowered free-flight tests at angles of attack from 0 degrees to 22 degrees (0.38 radian) and at calibrated airspeeds from 61 knots to 113 knots (31.38 to 58.13 meters/second). Flight data are compared with results from full-scale wind-tunnel tests of the same vehicle.
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Subject Category: 02
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Report Date: September 1965
No. Pages: 44
Keywords: Comparison; Drag; Low speed; M-2 lifting body.
- FLIGHT EVALUATION OF THE X-15 BALL-NOSE FLOW-DIRECTION SENSOR AS AN AIR-DATA SYSTEM , Technical Note
Authors: J. P. Cary and E. R. Keener
Report Number: NASA-TN-D-2923
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper assesses the suitability of the modified ball-nose system for obtaining Mach number and pressure altitude from pressure measurements at Mach numbers up to 5.3, altitudes up to 130,000 feet, and Reynolds number from 0.1 to 1.6 ¥ 10 to the 6th per foot. The results are compared with experimental and theoretical results for spheres.
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Subject Category: 35
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Report Date: July 1965
No. Pages: 21
Keywords: Air data systems; Atmospheric pressure; Flight tests; Flow direction indicators; Gas pressure.
- DESIGN AND OPERATIONAL CHARACTERISTICS OF A LUNAR-LANDING RESEARCH VEHICLE , Technical Note
Authors: D. R. Bellman and G. J. Matranga
Report Number: NASA-TN-D-3023
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper represents the significant technical details and research capabilities of a free-flight lunar-landing simulator as they existed at the time of the initial flights of the vehicle. The lunar-landing research vehicle (LLRV) consists of a pyramid-shaped structural frame with four truss-type legs. A pilot’s platform extends forward between two legs, and an electronics platform is similarly located, extending rearward. A jet engine is mounted vertically in a gimbal ring at the center of the vehicle. The LLRV is instrumented for research purposes. The data obtained are converted to digital form transmitted to a ground tape recorder by means of an 80-channel pulse-code-modulation type (PCM) telemetry system. Each channel can be read every 0.005 second, if desired.
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Subject Category: 15
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Report Date: September 1965
No. Pages: 52
Keywords: Lunar landing; Research vehicles.
- LONG-RANGE PROGRAM TO DEVELOP MEDICAL MONITORING IN FLIGHT-THE FLIGHT RESEARCH PROGRAM-I , Journal Article
Authors: James Roman
Report Number: H-378
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NASA’s Flight Research Center is conducting a long-range program designed to advance the state of the art in biomedical monitoring. Better knowledge of the physiological parameters used in monitoring the crew is one of major aims of the program. An instrumentation-development phase and a phase involving development of computer techniques for handling medical flight data both contribute to the overall program. The physiological-parameters-research phase and the instrumentation-development phase have yielded significant results after one year of operation.
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Subject Category: 52
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Report Date: June 1965
No. Pages: 5
Keywords: Computer techniques; In-flight monitoring; Medical phenomena; NASA programs.
Notes: AEROSPACE MEDICINE, VOL. 36, JUN. 1965, P. 514-518.
- FLIGHT PRESSURE DISTRIBUTIONS ON THE VERTICAL STABILIZERS AND SPEED BRAKES OF THE X-15 AIRPLANE AT MACH NUMBERS FROM 1 TO 6 , Technical Note
Authors: J. S. Pyle
Report Number: NASA-TN-D-3048
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper, the third in series on the X-15 surface-pressure distributions, presents flight-measured pressure distributions for the upper and lower vertical stabilizers with the speed brakes opened and closed. Data are shown for Mach numbers from 1 to 6 and angles of attack from 0 degree to 15 degree. Comparisons are made with wind-tunnel data and theory.
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Subject Category: 05
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Report Date: September 1965
No. Pages: 56
Keywords: Brakes (for arresting motion); Pressure distribution; Stabilizers (fluid dynamics); Transonic speed; X-15 aircraft.
- COMPARISON OF MEASURED AND CALCULATED TURBULENT HEAT TRANSFER IN A UNIFORM AND NONUNIFORM FLOW FIELD ON THE X-15 UPPER VERTICAL FIN AT MACH NUMBERS OF 4.2 AND 5.3 , Technical Memorandum
Authors: R. P. Banas
Report Number: NASA-TM-X-1136
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Turbulent heat-transfer coefficients and measured local static pressures were obtained in flight on the X-15 upper vertical fin with both a sharp and a blunt leading edge. The data are compared with calculated values. Calculated and measured Mach number profiles in the shear layer are also presented. Heat-transfer coefficients were obtained from measured skin temperatures at free-stream Mach numbers of approximately 4.2 and 5.3 and free-stream Reynolds numbers between 1.8 x l0(6) and 2.5 x l0(6) per foot. Comparisons of measured and calculated heat-transfer coefficients obtained in both a uniform flow field and a nonuniform flow field show that the heat-transfer coefficients calculated by Eckert’s reference-temperature method were from 32 percent to 57 percent higher than the measured values.
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Report Date: September 1965
No. Pages: 36
Keywords: Flow distribution; Hypersonic flight; Leading edges; Turbulent heat transfer; X-15 aircraft.
- EVALUATION OF THE LATERAL-DIRECTIONAL STABILITY AND CONTROL CHARACTERISTICS OF THE LIGHTWEIGHT M2-F1 LIFTING BODY AT LOW SPEEDS , Technical Note
Authors: H. J. Smith
Report Number: NASA-TN-D-3022
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper summarizes the lateral-directional stability and control characteristics investigated during the flight tests and compares some wind-tunnel data with the flight values. Performance data from the tests are reported.
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Subject Category: 02
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Report Date: September 1965
No. Pages: 36
Keywords: Directional control; Directional stability; Lateral stability; Lifting bodies; Stability.
- AN INVESTIGATION OF TERMINAL LUNAR LANDING WITH THE LUNAR LANDING RESEARCH VEHICLE , Technical Memorandum
Authors: G. J. Matranga and J. A. Walker
Report Number: NASA-TM-X-74475
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
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Subject Category: 01
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Report Date: January 1965
No. Pages: 30
Keywords: Astronaut performance; Conferences; Helicopters; Lunar landing modules; Tables (data).
Notes: Presented at AIAA Manned Space Flight Meeting, St. Louis, 11-13 Oct., 1965.
- OPERATIONAL AND PERFORMANCE CHARACTERISTICS OF THE X-15 SPHERICAL, HYPERSONIC FLOW-DIRECTION SENSOR , Technical Note
Authors: C. H. Wolowicz and T. D. Gossett
Report Number: NASA-TN-D-3070
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The basic design concepts, operational experiences (malfunctions, system characteristics, and system improvements), and flight-data measurements of the sensor are discussed and analyzed. The accuracy of the sensor in measuring angle of attack and angle of sideslip is assessed on the basis of an analysis of flight data and comparisons of these data with X-15 flight data determined from vane-type nose-boom installations and X-15 wind-tunnel data. Some practical limitations in the use of the sensor for extreme altitude applications are also considered.
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Report Date: November 1965
No. Pages: 21
Keywords: Hypersonic flow; Hypersonics; Sensors; X-15 aircraft.
- COMPONENT PERFORMANCE AND FLIGHT OPERATIONS OF THE X-15 RESEARCH AIRPLANE PROGRAM , Technical Memorandum
Authors: J. E. Love and W. R. Young
Report Number: NASA-TM-X-74527
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper discusses and analyzes the system and component failures that have occurred during the X-l5 program. Component performance is expressed in terms of its effect upon the entire operation, that is, as a failure rate per flight. Three representative systems are discussed: the engine system, the auxiliary power system, and the propellant system. Failures of shelf-stock components prior to their installation on the flight vehicles are also examined.
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Report Date: November 1965
No. Pages: 14
Keywords: Component reliability; Diagrams; Flight tests; Performance tests; X-15 aircraft.
Notes: Presented at the Ann. Symp. on Reliability, San Francisco, 25-27 Jan. 1966.
- LIFTING-BODY RESEARCH VEHICLES IN A LOW-SPEED FLIGHT TEST PROGRAM , Technical Memorandum
Authors: J. G. McTigue and M. O. Thompson
Report Number: NASA-TM-X-57412
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The lightweight M-2 flight test program has demonstrated the capability of a pilot to control lightweight lifting body during approach, flare, and landing. Further investigation is needed, however. Areas that are important, and that being investigated, include the use of optical landing systems, night and instrument capability, and thrust-augmented flare. A serious effort is required to reduce the complexity of the aerodynamic control system to prevent the lifting reentry vehicle from being seriously compromised in weight.
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Report Date: December 1965
No. Pages: 33
Keywords: Costs; Flight tests; Lifting bodies; M-2 lifting body; Wind tunnel tests.
Notes: Presented at ASSET/Advanced Lifting Reentry Technol. Symp., Miami, Fla., 14-16 Dec. 1965.
- PROGRESS OF THE X-15 RESEARCH AIRPLANE PROGRAM , Special Publication
Authors: Various
Report Number: NASA-SP-90
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
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Report Date: October 1965
No. Pages: 133
Keywords: Aerodynamic characteristics; Aircraft performance; Conferences; Flight tests; X-15 aircraft.
Notes: Conf. held at Edwards AFB, Calif., 7 Oct. 1965; sponsored by the AF, Navy, and NASA.
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