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    Experimental and computational flow-field results for an all-body hypersonic aircraft (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A comprehensive test program is defined which is being implemented in the NASA/Ames 3.5 foot Hypersonic Wind Tunnel for obtaining data on a generic all-body hypersonic vehicle for computational fluid dynamics (CFD) code validation. Computational methods (approximate inviscid methods and an upwind parabolized Navier-Stokes code) currently being applied to the all-body model are outlined. Experimental and computational results on surface pressure distributions and Pitot-pressure surveys for the basic sharp-nose model (without control surfaces) at a free-stream Mach number of 7 are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-185347 , NAS 1.26:185347 , National Aero-Space Plane Technology Symposium; Apr 24, 1989 - Apr 28, 1989; Sunnyvale, CA; United States
    Format: application/pdf
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