DNS of unsteady shock boundary layer interaction

A novel numerical scheme has been developed to simulate high speed viscous flows in complex geometries using unstructured grids. A characteristic–filter based shock capturing scheme is applied as a corrector step to a non–dissipative predictor scheme. This algorithm is being used to study shock turbulent boundary layer interactions and this paper presents the results of a turbulent flow at Mach 2.9 over a 24 compression corner. Turbulent boundary layer flow is generated by a natural laminar–turbulent transition using a roughness strip. This methodology results in a fully developed turbulent boundary layer which shows good agreement with available data. The solution of the compression corner flow is compared to experiments at similar conditions and the agreement is reasonable. An examination of the wall pressure signal shows the low frequency behavior characteristic of this problem. Simulations show that the shock affects the transition location and the skin friction coefficient of the incoming boundary layer.