Effect of Freestream Parameters on the Laminar Separation in Hypersonic Shock Wave Boundary Layer Interaction

Two-dimensional hypersonic flow over a ramped passage is computed on a finite volume framework using an in-house solver. van Leer’s Flux Vector Splitting (FVS) scheme is used to compute the inviscid fluxes. The gradients in the viscous flux terms are computed using the Green’s theorem. The effects of freestream parameters on the interaction between the boundary layer and the ramp-induced shock are investigated. For a given Reynolds number, the effects of freestream pressure and temperature on the laminar boundary layer separation are studied. It is seen that increase in freestream pressure reduces the flow separation; however increase in freestream temperature shifts the separation point upstream and the reattachment point downstream. Additionally the effect of Mach number at a given Reynolds number and freestream temperature on the boundary layer separation is discussed. Keywords:Hypersonic, shock, boundary layer, freestream