Simulation of Interaction Between Shock Wave and Boundary Layer in Supersonic Flow

In the study, interaction between shock wave and boundary layer is presented. The basic equations are the Navier-Stokes equations in Cartesian coordinate system. We applied supersonic flow over a forward facing step as an example. The multi-directional upwind finite difference method is employed for all the space derivative terms. It is very suitable to improve the accuracy when the flow direction is not well parallel to one of the coordinate lines. By the results, we could show exactly the separation of an oblique shock with a boundary layer developing on a flat plate.