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