Numerical Prediction of Supersonic Shock-boundary Layer Interaction

Report No. ARL-TR-5602
Authors: Vishal A. Bhagwandin and James DeSpirito
Date/Pages: July 2011; 46 pages
Abstract: Shock-boundary layer interaction was numerically simulated via steady-state, Reynolds-averaged Navier-Stokes methods using CFD++, a general purpose fluid flow solver. The simulations emulated experiments performed in two wind tunnel facilities, the Institut Universitaire des Systèmes Thermiques Industriels Wind Tunnel and the University of Michigan Wind Tunnel. Typical flow characteristics were captured, such as the location of the incident and reflected shock waves, boundary layer recirculation and separation, and increase in boundary layer displacement and momentum thicknesses. The numerical velocity components and Reynolds stresses in the boundary-layer compared fairly well with experimental data; however, improvement is still needed. The sensitivity of the simulations to the choice of turbulence model and grid density was also demonstrated.
Distribution: Approved for public release
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Last Update / Reviewed: July 1, 2011