Direct Numerical Simulation and Sub-Filter Scale Analysis for a Hypersonic Transitional Shock-Boundary Layer Interaction

In this paper, direct numerical simulation (DNS) and sub-filter scale analysis (SFS) are performed for hypersonic transitional shock-boundary layer interaction (SBLI) over a 15^◦ cold-wall compression ramp. The freestream Mach number and the Reynolds number based on the flat-plate length are 7.7 and 8.6 × 10^5, respectively, and the flow conditions and ramp geometry are representative of the experimental campaign conducted in the shock tunnel TH2 at the Shock Wave Laboratory of RWTH Aachen University. The DNS results including grid refinement suggest that the skin friction and Stanton number in the post-interaction region are sensitive to grid resolutions and numerical dissipation, whereas the wall pressure coefficient is less sensitive to these across the domain. A sub-filter scale analysis is included to investigate the challenges of large-eddy simulations (LES) of this case. The assessment of exact SFS shear stress shows the importance of accounting for spatial development in SFS modeling, where the activation of such models is only crucial in the post-interaction region.