Large-Eddy Simulation of a Supersonic Boundary Layer Using an Unstructured Grid

A Mach 3 adiabatic flat plate turbulent boundary layer is studied using large-eddy simulation (LES). The filtered compressible Navier-Stokes equations are solved on a three-dimensional unstructured grid of tetrahedral cells. A compressible extension of the rescaling-reintroducing process of Lund et al. is developed to generate the inflow conditions. The effect of the subgrid-scale motion is incorporated using two approaches, namely, monotone integrated LES (MILES) and the Smagorinsky subgrid-scale model. A detailed grid refinement study is performed

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