Dryden Technical Report Server
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- SUMMARY OF RAWINSONDE MEASUREMENTS OF TEMPERATURES, PRESSURE HEIGHTS, AND WINDS ABOVE 50,000 FEET ALONG A FLIGHT-TEST RANGE IN THE SOUTHWESTERN UNITED STATES , Technical Note
Authors: Terry J. Larson and Harold P. Washington
Report Number: NASA-TN-D-192
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Yearly, seasonal, diurnal, and 24-hour variations of temperatures, pressure heights, and winds in the 100-millibar to 2-millibar pressure range from rawinsonde data of four stations along a flight-test range in the southwestern United States are presented. This range, referred to as High Range, extends from Edwards, Calif., to Wendover, Utah, to accommodate flight operations of the X-15 and other high-performance craft. Comparisons of average temperatures and pressure heights are made with those of the U.S. Extension to the ICAO Standard Atmosphere.
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Subject Category: 47
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Report Date: January 1960
No. Pages: 83
Keywords: Atmospheric pressure; Atmospheric temperature; Pressure gradients; Temperature measurement; Test ranges.
- VERTICAL-TAIL LOADS MEASURED IN FLIGHT ON FOUR AIRPLANE CONFIGURATIONS AT TRANSONIC AND SUPERSONIC SPEEDS , Technical Note
Authors: Robert D. Reed
Report Number: NASA-TN-D-215
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Aerodynamic loads were obtained from the X-5 airplane, an F-100 with a small vertical tail, F-100 with a large vertical tail, and the X-1E airplane. Effects of sideslip angle, rudder deflection, and Mach number are presented for trim flight at altitudes from 40,000 feet to 70,000 feet and at Mach numbers from 0.70 to 2.08. Comparisons are made with simple theoretical methods of estimating the loads. Also, the total directional stability for each airplane as calculated by use of vertical-tail loads is shown.
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Subject Category: 05
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Report Date: February 1960
No. Pages: 34
Keywords: Aerodynamic loads; Aircraft configurations; Directional stability; Supersonic speed; Tail assemblies.
- FLIGHT TESTS OF A TWIN-DUCT INDUCTION SYSTEM FOR A MACH NUMBER RANGE OF 0.78 TO 2.07 , Technical Memorandum
Authors: J. Nugent and B. G. Powers
Report Number: NASA-TM-X-281
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Time histories of several airplane, engine, and induction-system parameters are presented for maneuvers made at altitude of 26,000 feet, 40,000 feet, and 55,000 feet over a Mach number range of 0.78 to 2.07. A time history of a push-down-turn maneuver at 40,000 feet is also presented. Comparisons of the data were made to show the effects of angle of attack. Mach number, altitude, and duct bypass area on the induction system parameters.
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Subject Category: 01
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Report Date: September 1960
No. Pages: 44
Keywords: Bypasses; Ducts; Flight tests; Intake systems; Mach number.
- REVIEW OF TECHNIQUES APPLICABLE TO THE RECOVERY OF LIFTING HYPERVELOCITY VEHICLES , Technical Memorandum
Authors: G. J. Matranga and J. Weil
Report Number: NASA-TM-X-334
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: A general review of piloting problems concerned with the recovery phase of lifting hypervelocity vehicles is presented. A short discussion is offered pertinent to the maneuvering capabilities and piloting techniques applicable to the initial approach phase of gliders with low lift-drag ratios. The principal emphasis concerns factors affecting the final approach and landing operation of these gliders. The results of general flight studies as well as recent experience obtained in the approach and landing of the X-15 research airplane are reviewed. Finally, a definition of the limits of piloted flared landings is developed.
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Subject Category: 52
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Report Date: September 1960
No. Pages: 17
Keywords: Hypersonic aircraft; Lifting bodies; Lifting reentry vehicles; X-15 aircraft.
- DYNA-SOAR STEP 1 FLIGHT TEST PROGRAM , Conference Paper
Authors: T. F. Baker, H. G. Russell and B. L. Schofield
Report Number: H-163
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: None available.
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Subject Category: 01
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Report Date: January 1960
No. Pages: 14
Keywords: Atmospheric entry; Conferences; Flight tests; Gliders; X-20 aircraft.
Notes: In its Joint Conf. on Lifting Manned Hypervelocity and Reentry Vehicles, part 2 p 311-324.
- INSTRUMENTATION AND COMMUNICATIONS CONSIDERATIONS , Conference Paper
Authors: G. M. Truszynski and P. O. Lindfors
Report Number: H-165
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: None available.
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Subject Category: 01
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Report Date: January 1960
No. Pages: 10
Keywords: Atmospheric entry; Communication equipment; Conferences; Gliders; X-20 aircraft.
Notes: In its Joint Conf. on Lifting Manned Hypervelocity and Reentry Vehicles, part 2 p 325-334.
- UTILIZATION OF THE PILOT DURING BOOST PHASE OF THE STEP 1 MISSION , Conference Paper
Authors: E. C. Holleman
Report Number: H-166
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
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Subject Category: 01
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Report Date: January 1960
No. Pages: 12
Keywords: Atmospheric entry; Conferences; Mission planning; Pilots (personnel); X-20 aircraft.
Notes: In its Joint Conf. on Lifting Manned Hypervelocity and Reentry Vehicles, part 2 p 261-272.
- SIMULATION REQUIREMENTS FOR THE DEVELOPMENT OF ADVANCED MANNED MILITARY AIRCRAFT , Technical Memorandum
Authors: E. C. Holleman and M. Sadoff
Report Number: NASA-TM-X-54672
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: The present state of the art of the piloted flight simulator leaves no major deterrent to the mechanization of required simulators for the design of present or future manned military airplanes. The fixed-base simulator with adequate presentation and controls is completely satisfactory for the investigation of a wide range of airplane problems. However, there are some areas which require some form of motion stimulus. Other areas remain where simulator requirements are not yet resolved, but work is continuing to better define these simulator requirements.
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Subject Category: 01
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Report Date: August 1960
No. Pages: 8
Keywords: Aircraft design; Analog computers; Attack aircraft; Flight simulators; Military aircraft.
- PRELIMINARY FULL-SCALE POWER-OFF DRAG OF THE X-15 AIRPLANE FOR MACH NUMBERS FROM 0.7 TO 3.1 , Technical Memorandum
Authors: Edwin J. Saltzman
Report Number: NASA-TM-X-430
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Drag characteristics have been obtained for the X-15 airplane during unpowered flight. These data represent a Mach number range from about 0.7 to 3.1 and a Reynolds number range from 13.9 x 10(exp 6) to 28 x 10(exp 8), based on the mean aerodynamic chord. The full-scale data are compared with estimates compiled from several wind-tunnel facilities. The agreement between wind-tunnel and full-scale supersonic drag, uncorrected for Reynolds number effects, is reasonably close except at low supersonic Mach numbers where the flight values are significantly higher.
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Subject Category: 02
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Report Date: December 1960
No. Pages: 26
Keywords: Aerodynamic drag; Airfoil profiles; Mach number; Supersonic drag; Wind tunnel tests.
- TRAINING ASPECTS OF THE X-15 PROGRAM
Authors: R. E. Day
Report Number: H-201
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Various training aids in the development of the X-15 program are presented. Future flight data obtained in more critical control areas will afford the unique opportunity to assess the true value of these training aids for the X-15 and to establish training requirements for future vehicles.
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Subject Category: 01
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Report Date: August 1960
No. Pages: 10
Keywords: Astronaut training; Centrifuging; Daytime; Education; Missiles.
Notes: IN THE TRAINING OF ASTRONAUTS. WASHINGTON, NATIONAL RESEARCH COUNCIL, 1961. P. 5-14.
- REVIEW OF TECHNIQUES APPLICABLE TO THE RECOVERY OF LIFTING HYPERVELOCITY VEHICLES , Technical Memorandum
Authors: Joseph Weil and Gene J. Matranga
Report Number: NASA-TM-X-67563
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: No abstract available.
Distribution/Availability: Unclassified - Unlimited
Subject Category: 01
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Report Date: January 1960
No. Pages: 14
Keywords: Conferences; Gliders; Hypersonic vehicles; Lifting bodies; Spacecraft recovery.
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