Three-dimensional shock / turbulent boundary layer interaction in a simulated scramjet inlet

The interaction of shock waves generated in a scramjet inlet with the boundary layer on the walls can result in a complex flowfield. This can have important implications for the performance of the inlet. Understanding the flow physics and predicting them reliably is a challenging task. In the current paper, the three-dimensional flowfield generated by the interaction of the cowl shock with the boundary layers on the walls of the inlet is studied computationally. The solution is analysed in detail and a description of the flow topology is presented. The side wall boundary layer is found to separate and roll up into a large longitudinal vortex. The flow is also characterized by the formation of a complex pattern of shock waves interacting with each other. The flowfield has striking resemblance to the double-fin configuration that has been studied extensively in literature.