Abstract
A preliminary LES study of the interaction of a Mach 3 adiabatic turbulent boundary layer with the shock system generated by a 25’ compression corners is presented. The filtered compressible Navier-Stokes equations are solved on a three-dimensional unstructured grid of tetrahedral cells using a finite volume formulation. The inflow conditions are produced by a resealing-reintroducing method. The subgrid scale motions are modeled using the Monotone Integrated Large Eddy Simulation (MILES) method. The incident shock causes separation of the boundary layer upstream of the point of impingement of the primary shock, with a secondary shock forming near the separation. Qualitative data on the flowfield structure are presented.
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