Numerical Prediction of Shock-Boundary Layer Interaction between a Pair of Fins in Hypersonic Flow

Shock-boundary layer interaction was numerically simulated via steady-state Reynoldsaveraged Navier-Stokes numerical methods. The simulations emulated the Kussoy and Horstman experimental test case involving a pair of fins mounted on a flat plate in a Mach 8.3 hypersonic flow. Qualitative numerical results revealed typical aerodynamic flow structures, such as propagating shock trains, growth, separation and reattachment of the boundary layer and aerodynamic heating. Quantitative comparisons with experiment show fair to very good predictions of pressure, and fair to poor predictions of heat flux. Sensitivities to turbulence modeling and grid resolution were also demonstrated.