Numerical Study on Shock Wave Interaction over Compression Corner with 30 deg. in Hypersonic Flow

摘要

The shock wave interactions over a compression corner with 30 deg. in hypersonic flow were estimated by using the numerical simulations. The shock structure becomes complex as decreasing the angle of attack. The present shock structures is similar to Type Ⅵ for α = 0,10 deg. and Type Ⅴ for α = 15 deg., respectively. The longitudinal streaks in the surface heat flux appear on the model surface. This distribution was caused by the Goertler vortices. The comparison of pressure and heat flux on the surface between the numerical and experimental results agree well for all angles of attack. The peak heat flux for α=20 deg. becomes four times larger than that for α=0 deg. because of the impinging shock on the surface.