Flow Separation In Shock Wave Boundary Layer Interactions At Hypersonic Speeds
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Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds
Author: National Aeronautics and Space Adm Nasa
language: en
Publisher:
Release Date: 2018-10-28
An 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. Hamed, A. Unspecified Center...