This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists of selected configurations where the only characteristic length in the iteration is the incoming boundary layer thickness. It consists 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 empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling, and the methods of detecting separation are discussed.
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January 1994
Research Papers
Flow Separation in Shock Wave Boundary Layer Interactions
A. Hamed,
A. Hamed
Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati, Cincinnati, OH 45221
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A. Kumar
A. Kumar
Theoretical Flow Physics Branch, NASA Langley Research Center, Hampton, VA 23665-5225
Search for other works by this author on:
A. Hamed
Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati, Cincinnati, OH 45221
A. Kumar
Theoretical Flow Physics Branch, NASA Langley Research Center, Hampton, VA 23665-5225
J. Eng. Gas Turbines Power. Jan 1994, 116(1): 98-103 (6 pages)
Published Online: January 1, 1994
Article history
Received:
February 21, 1992
Online:
April 24, 2008
Citation
Hamed, A., and Kumar, A. (January 1, 1994). "Flow Separation in Shock Wave Boundary Layer Interactions." ASME. J. Eng. Gas Turbines Power. January 1994; 116(1): 98–103. https://doi.org/10.1115/1.2906816
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