A hybrid RANS/LES framework is proposed to simulate a zero pressure gradient supersonic turbulent boundary layer over a flat plate. A delayed detached eddy simulation (DDES) framework is used. A non-zonal approach is used to transition between a SST k − ω RANS model and a compressible dynamic Smagorinsky model. A finite volume based flow solver using a sixth-order compact interpolation method is developed for the purpose. The numerical method is validated using a Mach 2 zero pressure gradient flat plate turbulent boundary layer simulation. © 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.