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Experimental and computational flow-field results for an all-body hypersonic aircraftA 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.
Document ID
19890016582
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cleary, Joseph W. (Eloret Corp. Sunnyvale, CA, United States)
Date Acquired
September 6, 2013
Publication Date
June 7, 1989
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:185347
NASA-CR-185347
Meeting Information
Meeting: National Aero-Space Plane Technology Symposium
Location: Sunnyvale, CA
Country: United States
Start Date: April 24, 1989
End Date: April 28, 1989
Accession Number
89N25953
Funding Number(s)
CONTRACT_GRANT: NCC2-416
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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