Effect of Mach number and Reynolds number on a normal shock-wave/turbulent boundary-layer interaction

摘要: Experimental values of wall pressure and skin friction have been obtained for Mach numbers from 1.32 to 1.48 Reynolds 8.5 x 10 the 6th 225 6th. Increasing number reduces shear promotes incipient separation. variations little effect except at lowest value where flow abruptly approaches Comparisons are made with solutions time-dependent, Reynolds-averaged, Navier-Stokes equations incorporating a two-equation, Wilcox-Rubesin turbulence model. The computations in agreement experimental results. Additional numerical results indicated that wind-tunnel walls constrained suppressed formation separation bubble shock wave.