A finite volume based numerical method for simulating supersonic turbulent boundary layer over a flat plate is suggested. A sixth-order compact interpolation method is used for computing fluxes at the cell interfaces. A rescaling method for generating inflow turbulence is discussed to provide realistic inflow conditions at the inlet. DNS and LES are conducted for Mach 2 zero pressure gradient turbulent boundary layer. Mean velocity profiles and turbulent intensities are validated. © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.