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  • 1
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    Explanation of the hypersonic longitudinal stability problem: Lessons learned (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Inviscid and viscous CFD codes have been applied to a modified Space Shuttle orbiter geometry to investigate differences between preflight aerodynamic predictions and aerodynamic data from hypersonic reentry flight. Flow field solutions were obtained for wind tunnel conditions and flight conditions to assess Mach number, real-gas, and viscous effects on the reentry aerodynamics of the orbiter. Based on the CFD studies, a methodology model has been developed to (1) extrapolate wind tunnel data to flight conditions and (2) calculate a DCM for use with the Aerodynamic Design Data Book. Comparisons are made with selected flight data. Results of the study indicate that the differences between flight and pre-STS-1 predictions of hypersonic pitching moment are primarily due the to Mach number and real-gas effects.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 347-381
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Addressing the hypersonic simulation problem (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 334-341
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Addressing the hypersonic simulation problem (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The hypersonic simulation problem is solved by the meshing of bench-marked experimental data with results from validated computational fluid dynamic codes. The example presented is for the reentry of the Space Shuttle Orbiter. Mach number effects were assessed by parametrically varying free-stream Mach number and angle of attack in a series of inviscid, perfect-gas computations carried out on a modified Orbiter geometry. Real-gas effects were determined by making calculations at specific points of the reentry trajectory using equilibrium air thermodynamics and comparing with corresponding perfect-gas computations. Viscous computations were also made for both the basic Orbiter body and control surfaces. A methodology is developed that permits the extrapolation of wind tunnel data to flight situations, providing a solution to the hypersonic simulation problem.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-9775
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Atmospheric heating of meteors. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A theoretical model of the radiating metallic gas produced about an iron meteor entering the earth's atmosphere is discussed. Numerical results are presented for a 0.1 cm diameter iron meteor traveling at 15 km/sec at an altitude of 100 km above the earth. It is shown that collisions between the expanding iron gas and the air molecules produce a radiating gas shell a few meters thick which is located many meters ahead of the meteor core. Temperature, pressure, and density distributions are presented as functions of radial distance and angle for several initial meteor conditions.
    Keywords: SPACE SCIENCES
    Type: AIAA PAPER 72-204 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 17, 1972 - Jan 19, 1972; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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