Shock/Turbulent Boundary Layer Interactions

The shock wave/turbulent boundary interaction exists for all supersonic or hypersonic vehicles. In this research, the 3D Reynolds averaged Navier-Stokes equations with full Reynolds stress transport equation model are solved to simulate the shock wave/turbulent boundary layer interaction caused by asymmetric crossing shock waves at Mach number 4.0. The pressure distribution agrees well with the experiment, but the heat transfer coefficient largely deviates from the experiment. More advanced turbulent boundary layer simulation such as large eddy simulation or direct numerical simulation are needed to improve the prediction accuracy.

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