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Reynolds number effects on shock-wave turbulent boundary-layer interactions - A comparison of numerical and experimental resultsAn experiment is described that tests and guides computations of a shock-wave turbulent boundary-layer interaction flow over a 20-deg compression corner at Mach 2.85. Numerical solutions of the time-averaged Navier-Stokes equations for the entire flow field, employing various turbulence models, are compared with the data. Each model is critically evaluated by comparisons with the details of the experimental data. Experimental results for the extent of upstream pressure influence and separation location are compared with numerical predictions for a wide range of Reynolds numbers and shock-wave strengths.
Document ID
19770036939
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Horstman, C. C. (NASA Ames Research Center Experimental Fluid Dynamics Branch, Moffett Field, Calif., United States)
Settles, G. S. (Princeton Combustion Laboratories/Flow Research, Inc. Princeton, N.J., United States)
Vas, I. E. (DCW Industries, Inc. Sherman Oaks, CA, United States)
Bogdonoff, S. M. (Princeton University Princeton, N.J., United States)
Hung, C. M. (DCW Industries Sherman Oaks, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 77-42
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Los Angeles, CA
Start Date: January 24, 1977
End Date: January 26, 1977
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
77A19791
Funding Number(s)
CONTRACT_GRANT: F44620-75-C-0080
CONTRACT_GRANT: NSG-2114
Distribution Limits
Public
Copyright
Other

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