Shock/turbulent boundary layer interaction (STBLI) manifests across a diverse array of supersonic flows: transonic airfoil, supersonic inlet, off-design nozzle, and near control flap. The practical impact of STBLI is very detrimental and necessitates design compromise, such as thermodynamic surface loading, low-frequency unsteadiness and pressure loss. We have developed an advanced high-order and high fidelity in-house code to solve compressible flow. Our investigation into the internal physics and mechanisms of STBLI employs Direct Numerical Simulation (DNS) in conjunction with parallel supercomputing technology.