Numerical Prediction of Supersonic Shock- Boundary Layer Interaction

Shock-boundary layer interaction was numerically simulated via steady-state, Reynolds-averaged NavierStokes methods using CFD++, a general purpose fluid flow solver. The simulations emulated experiments performed in two wind tunnel facilities, namely, the Institut Universitaire des Systemes 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.