High Fidelity Simulations of Supersonic Intakes

A parametric study of Multiple Shock Wave Boundary Layer Interactions is presented in this paper. All results were obtained using the in-house CFD solver of Glasgow University. Such interactions often occur in high-speed intakes which have recently seen a renewed interest. Simulations of a multiple shock wave boundary layer interaction in a rectangular duct were first performed and the results were compared to the experiments. Using the same numerical setup a parametric study investigating the effect of Mach number, Reynolds number and confinement on the baseline solution was then performed. Efficiency metrics were also define to quantify the interactions. The results show that Reynolds-stress based turbulence models are better suited than linear models. The corner separations affect the separation at the centreline which in turn alters the structure of the initial shock and the subsequent interaction. Reduced confinement is found to be beneficial for higher pressure recovery. Finally, results for a more realistic geometry (fore-body with an intake) featuring an oblique and multiple shock wave boundary layer interactions are presented