Numerical solutions of finite difference approximations to the compressible Navier‐Stokes equations have been calculated for the steady two‐dimensional flow of a supersonic stream and boundary layer over a rectangular base. The configuration represents a model problem for the laminar near wake of a blunt‐based body. Solutions have been obtained for a range of Reynolds numbers (based on the base half‐height and the inflow conditions) less than 1000 at Mach numbers between 2 and 4. Both the cases of an adiabatic wall and a constant wall temperature have been computed. The important features of the flow, such as the expansion around the corner, the separation of the boundary layer, the recirculation region, the recompression, and the formation of the wake shock, are illustrated in the results. Also shown are the changes in the solutions with the variation of the Reynolds number, the Mach number, and the wall temperature conditions.

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