Shock waves generated at different parts of vehicle interact with the boundary layer over the surface at high Machflows. The adverse pressure gradient across strong shock wave causes the flow to separate and peak loads are generated atseparation and reattachment points. The size of separation bubble in the shock boundary layer interaction flows depends onvarious parameters. Reynolds-averaged Navier-Stokes equations using the standard two-equation k-ω turbulence model is usedin simulations for hypersonic flows over compression corner. Different deflection angles, including ranging from 15o to 38o, are simulated at Mach 9. 22 to study its effect on separated flow. This is followed by a variation in the Reynolds number basedon the boundary layer thickness, Re from 1x105 to 4x105. Simulations at different constant wall conditions Tw of cool, adiabatic, and hot are also performed. Finally, the effect of free stream Mach numbers M∞ , ranging from 5 to 9, on interactionregion is studied. It is observed that an increase in parameters, , Re , and Tw results in an increase in the separation bubblelength, Ls, and an increase in M∞ results in the decrease in Ls.