Simulations of Incident Shock Boundary Layer Interactions

© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved. We examine the effects of varying the tunnel width to height ratio, the boundary layer thickness, and the incident shock angle on the shock boundary layer interaction of an incident oblique shock with a turbulent boundary layer. The computational domain is a simplified representation of typical wind tunnel experiments where the top wall of the tunnel is not modeled; only the flow conditions imposed by the shock are modeled on the top of the computational domain. We also examine the differences that arise from addition of Quadratic Constitutive terms to the flow equations. These terms are needed to give rise to corner flow vortices in tunnel flows without shocks and have a significant effect on the side wall corner flow that increases as the strength of shockwave boundary layer interaction increases.