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  • 1
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    NASA participation in the AMST program (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objectives of the NASA Advanced Medium STOL Transport Experiments Program are discussed and several of the NASA experiments currently implemented and conducted on the YC-14 and YC-15 prototype aircraft are described. Emphasis is placed on experiments related to powered lift aerodynamics and acoustics.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 465-478
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Stratosphere and mesosphere density-height profiles obtained with the x-15 airplane (1963)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Stratosphere and mesosphere density-height profiles obtained with X-15 aircraft
    Keywords: GEOPHYSICS
    Type: NASA-TM-X-51734
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wind-tunnel investigation of the flow field beneath the fuselage of the X-15 airplane at Mach numbers from 4 to 8 (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel study of flow field beneath X-15 aircraft fuselage at supersonic to hypersonic speeds
    Keywords: AIRCRAFT
    Type: NASA-TM-X-1469
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-tunnel force and pressure tests of rocket-engine nozzle extensions on the 0.0667-scale X-15-2 model at supersonic and hypersonic speeds (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel force and pressure tests of rocket engine nozzle extensions on X-15-2 model at supersonic and hypersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1759
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wind-tunnel calibration and requirements for in-flight use of fixed hemispherical head angle-of-attack and angle-of-sideslip sensors (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-tunnel tests were conducted with three different fixed pressure-measuring hemispherical head sensor configurations which were strut-mounted on a nose boom. The tests were performed at free-stream Mach numbers from 0.2 to 3.6. The boom-angle-of-attack range was -6 to 15 deg, and the angle-of-sideslip range was -6 to 6 deg. The test Reynolds numbers were from 3.28 million to 65.6 million per meter. The results were used to obtain angle-of-attack and angle-of-sideslip calibration curves for the configurations. Signal outputs from the hemispherical head sensor had to be specially processed to obtain accurate real-time angle-of-attack and angle-of-sideslip measurements for pilot displays or aircraft systems. Use of the fixed sensors in flight showed them to be rugged and reliable and suitable for use in a high temperature environment.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6986 , H-702
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Local flow measurements at the inlet spike tip of a Mach 3 supersonic cruise airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field at the left inlet spike tip of a YF-12A airplane was examined using at 26 deg included angle conical flow sensor to obtain measurements at free-stream Mach numbers from 1.6 to 3.0. Local flow angularity, Mach number, impact pressure, and mass flow were determined and compared with free-stream values. Local flow changes occurred at the same time as free-stream changes. The local flow usually approached the spike centerline from the upper outboard side because of spike cant and toe-in. Free-stream Mach number influenced the local flow angularity; as Mach number increased above 2.2, local angle of attack increased and local sideslip angle decreased. Local Mach number was generally 3 percent less than free-stream Mach number. Impact-pressure ratio and mass flow ratio increased as free-stream Mach number increased above 2.2, indicating a beneficial forebody compression effect. No degradation of the spike tip instrumentation was observed after more than 40 flights in the high-speed thermal environment encountered by the airplane. The sensor is rugged, simple, and sensitive to small flow changes. It can provide accurate imputs necessary to control an inlet.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6987 , H-722
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Research instrumentation requirements for flight/wind-tunnel tests of the YF-12 propulsion system and related flight experience (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Symposium on Instrumentation for airbreathing propulsion; Sep 19, 1972 - Sep 21, 1972; Monterey, CA
    Format: text
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    NASA TECHNICAL REPORTS
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