The mechanisms of boundary layer separation caused by Shock /Boundary layer Interaction(SWBLI) in scramjet inlet and its control with Magnetohydrodynamics(MHD) were investigated numerically with a three dimensional CFD code,within which HLLE schemes,LU-SGS method,sst-kω turbulence model and multiblock structure grid were used.The results show that the numerical wall pressure agrees well with the experimental data,and the height of separation zone in the shoulder of scramjet inlet occupies 1/3 size of the throat height.With MHD accelerating the boundary layer,the separation in the scramjet inlet is eliminated,and the total pressure recovery coefficient is increased from 0.502 to 0.56,the flow field distortion parameter at the scramjet inlet throat zone is decreased by 18.6%.
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