Flow Separation in Shock Wave Boundary Layer Interactions

[+] Author and Article Information
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 116(1), 98-103 (Jan 01, 1994) (6 pages) doi:10.1115/1.2906816 History: Received February 21, 1992; Online April 24, 2008


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.

Copyright © 1994 by The American Society of Mechanical Engineers
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