Investigation of Wall Temperature Effects on Shock-Wave Turbulent Boundary Layer Interaction in a Compression Ramp using Large-Eddy Simulations

Shock-wave turbulent boundary layer interaction (STBLI) occurring within high-speed aerospace applications is characterized by unsteady and nonlinear multi-scale and multi-physics phenomena such as boundary layer thickening, shock dynamics, shock-induced separation/reattachment, intense thermo-mechanical loading, temperature effects, and low-frequency unsteadiness. The present study examines the effects of wall temperature on the features of STBLI in terms of the ratio of wall temperature to recovery temperature (T_w/T_r). The computational setup follows past studies and corresponds to a supersonic flow over a 24-degree compression ramp with a freestream Mach number of 2.9 and the freestream Reynolds number per unit millimeter of 5581.4. The dynamic one-equation model is used to perform wall-resolved large-eddy simulation (LES) at T_w/T_r = 0.6, 1.14, 1.4, and 2. The results are examined to assess the ability of LES to capture the effects of wall temperature on the statistics of the separation bubble by comparing with reference results from the literature. Additionally, the results are analyzed to examine the non-equilibrium aspects of the near-wall turbulence dynamics in the vicinity of the separation bubble.