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Hypersonic flow separation in shock wave boundary layer interactionsAn assessment is presented for the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists mainly of two dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the subsequent changes in the flow empirical correlations for incipient separation are reviewed. The effects of the Mach number, Reynolds number, surface cooling and the methods of detecting separation are discussed. The pertinent experimental data for the separated flow characteristics in separated turbulent boundary layer shock interaction are also presented and discussed.
Document ID
19930035432
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hamed, A.
(Cincinnati Univ. OH, United States)
Kumar, Ajay
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
ASME PAPER 92-GT-205
Meeting Information
Meeting: ASME, International Gas Turbine and Aeroengine Congress and Exposition
Location: Cologne
Country: Germany
Start Date: June 1, 1992
End Date: June 4, 1992
Sponsors: ASME
Accession Number
93A19429
Funding Number(s)
CONTRACT_GRANT: NAS1-18458
Distribution Limits
Public
Copyright
Other

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