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Numerical Calculations of Shock-Wave/Boundary-Layer Flow InteractionsThe paper presents results of calculations for 2-D supersonic turbulent compression corner flows. The results seem to indicate that the newer, improved kappa-epsilon models offer limited advantages over the standard kappa-epsilon model in predicting the shock-wave/boundary-layer flows in the 2-D compression corner over a wide range of corner angles and flow conditions.
Document ID
19950019657
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huang, P. G. (Eloret Corp. Palo Alto, CA., United States)
Liou, W. W. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1994
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
CMOTT-94-4
NAS 1.15:106694
E-9049
ICOMP-94-16
NASA-TM-106694
Report Number: E-9049
Report Number: ICOMP-94-16
Report Number: NASA-TM-106694
Report Number: CMOTT-94-4
Report Number: NAS 1.15:106694
Meeting Information
Meeting: International Conference on Flow Interactions
Country: Hong Kong
Start Date: September 5, 1994
End Date: September 9, 1994
Accession Number
95N26077
Funding Number(s)
PROJECT: RTOP 505-90-5K
CONTRACT_GRANT: NCC3-233
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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