Prediction of aerothermal characteristics of a generic hypersonic inlet flow

The accurate prediction of aerothermal surface loading is paramount importance for the design high speed flight vehicles. In this work, we consider numerical solution hypersonic flow over a double-finned geometry, representative inlet an air-breathing vehicle, characterized by three-dimensional intersecting shock-wave/turbulent boundary-layer interaction at Mach 8.3. High Reynolds numbers ($Re_L \approx 11.6 \times 10^6$ based on free-stream conditions) and presence cold walls ($T_w/T_o 0.27$) leading to large near-wall temperature gradients necessitate use wall-modeled large-eddy simulation (WMLES) in order make calculations computationally tractable. comparison WMLES results with experimental measurements shows good agreement time-averaged heat flux wall pressure distributions, predictions show reduced errors respect than prior RANS calculations. favorable comparisons are obtained using LES model equilibrium boundary layer approximations despite numerous non-equilibrium conditions including three dimensionality, shock-boundary interactions, separation. Lastly, it also demonstrated that semi-local eddy viscosity scaling (in lieu commonly used van Driest scaling) necessary accurately predict fluxes.