Numerical simulations of shock/boundary layer interactions using time-dependent modeling techniques: A survey of recent results

Supersonic or hypersonic flows within and around flight vehicles inevitably involve interactions of strong shock waves with boundary layers. Flows within inlet/isolator configurations, and flows induced by control surface deflections are some examples. Such interactions are time dependent in nature and are often subject to low-frequency, large-scale motion that induces local pressure and heating loads. With recent increases in available computer power, it has now become possible to simulate such interactions at experimentally relevant Reynolds numbers using time-dependent techniques, such as direct numerical simulation (DNS), large-eddy simulation (LES), and hybrid large-eddy simulation/Reynolds-averaged Navier-Stokes (LES-RANS) methods. This paper will survey some recent work in this area and will describe insights in shock/boundary layer interaction physics gained by using these high-fidelity methods. Attention will be focused on studies that compare directly with experimental data at the same (or nearly the same) Reynolds number. Challenges in the application of these techniques to even more complicated high-speed flow fields are also outlined.