About the Assessment of Heat Flux and Skin Friction of the DLR TAU-code for Turbulent Supersonic Flows

Abstract

The correct prediction of skin friction and surface heat flux by CFD tools is an important prerequisite for the design of hypersonic flight vehicles. Results of a test campaign of a flow past a flat plate configuration with an impinging oblique shock carried out in the Ludwieg Tube Facility of DLR Göttingen were used to assess the applicability and accuracy of the DLR TAU-code at respective flow conditions. A shock-wave/turbulent boundary layer interaction (SWTBLI) on the flat plate model was created with a planar shock generator at different incidence angles. This two dimensional test case involving the flat plate flow and the interaction of an oblique shock with the turbulent boundary layer is well documented with various measurements like wall pressure, boundary layer velocity profiles, skin friction, and heat flux, and offers a good basis for the assessment of the two latter variables for the DLR TAU-code. The assessment includes grid studies, the influence of various turbulence models as well as the external turbulence intensity set in the calculations.