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Supersonic flow over a compression expansion corner is simulatednumerically. Three-dimensional Navier-Stokes equations have been solvedovercompression expansion corner for validation of in- house three dimensional Navier stokes code. Steger and warming flux vector splitting scheme has been used. Simulation captures all the features of complex flow problem including formation of oblique shock, expansion wave and their reflection and interaction. The results compare very well with the analytical data.