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Documentation of Two- and Three-Dimensional Hypersonic Shock Wave/Turbulent Boundary Layer Interaction FlowsExperimental data for a series of two- and three-dimensional shock wave/turbulent boundary layer interaction flows at Mach 7 are presented. Test bodies, composed of simple geometric shapes, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface-pressure and heat-transfer distributions as well as limited mean-flow-field surveys in both the undisturbed and the interaction regimes. The data are presented in a convenient form for use in validating existing or future computational models of these generic hypersonic flows.
Document ID
19890010729
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Kussoy, Marvin I. (Eloret Corp. Sunnyvale, CA., United States)
Horstman, Clifford C. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-101075
A-89048
NAS 1.15:101075
Accession Number
89N20100
Funding Number(s)
CONTRACT_GRANT: NCC2-452
PROJECT: RTOP 505-80-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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