Computation of high-speed turbulent flows using conven- tional turbulence models developed for incompressible flows can lead to significant errors. This is especially true for high-speed vehicles where the Mach number ranges from low subsonic at the nose to hypersonic values along the body. The flow field is fur- ther complicated by boundary layer transition on fore-body, flow separation behind the vehicle, and turbulent free shear layer recompression in the reattachment region. Several compressibility corrections to conventional turbulence models have been pro- posed to account for these high Mach number effects. This pa- per evaluates such modifications to one- and two-equation tur- bulence models. The test case considered is the flow around a hypersonic re-entry configuration with a large recirculation re- gion behind the vehicle. Issues pertaining to the implementation of the models and their modifications to a practical configuration are discussed. The effect of the different models and compress- ibility corrections are studied in terms of the predicted boundary layer transition location, size of the recirculation region, and the resulting pressure and heat transfer rate on the vehicle.