Numerical Investigation of Mach 2.5 Axisymmetric Turbulent Shock Wave Boundary Layer Interactions

Shock wave boundary layer interactions are common to both supersonic and hypersonic inlet flows. Wall-resolved implicit large-eddy simulations of a canonical Mach 2.5 axisymmetric shock interaction experiment at Glenn Research Center were carried out. A conical was generated with centerbodies 16 deg half-angle cone. The centerbody radii 9.2% 14.7% the test section diameter. interacted turbulent on inside cylindrical section. experimental Reynolds number based diameter six million. For simulations, reduced by factor 10 lower computational expense. separates for separation is stronger larger radius. Frequency spectra spanwise-averaged wall-pressure coefficient reveal low-frequency content Strouhal numbers length between 0.02 0.05 in vicinity mid-frequency 0.1 0.2 downstream separation. proper orthogonal decomposition captures spanwise coherent structures 0.03–0.04 over region streamwise 0.1–0.4.