Shock-Wave/Boundary-Layer interaction is a contradictory phenomenon that commonly occurs in high-speed flows, which causes large flow unsteadiness and pressure fluctuation loads. Separation due to strong interaction between Shock-Wave and boundary layer causes mass blockage and high heat transfer rate over high-speed intakes. In this present study, a numerical analysis of Shock-Wave/Boundary layer interaction was carried out over blunted cone/flare at hypervelocity speed. The chemically reacting and non-reacting hypervelocity flow had been studied. Numerical validation confirms no significant difference between chemically reacting and chemically non-reacting flow for the selected experimental data. Shock- Wave induced separation observed upstream of 30-degree corner. By employing an isothermal lowtemperature wall, the local momentum of the flow had been increased, which significantly reduces the separation.