Prediction of hypersonic turbulent ow eld with non-equilibrium thermo-chemistry around re-entry vehicles is a challenging task. The predictions error are high due to the uncertainties in the turbulence models. In this paper, ow eld around the Fire II re-entry module is computed using the Reynold-averaged Navier Stokes method. Five species air chemistry and a two-temperature vibrational relaxation model is used to compute the reacting ow around the vehicle. The freestream conditions correspond to the lowest altitude, and therefore highest Reynolds number, for which in-ight measurements are available. One-equation Spalart-Allmaras and two-equation k -! models are used for turbulence closure, and the model predictions are compared with in-ight measurements of afterbody pressure and heat transfer rate. In addition, the eect of turbulence and thermo-chemistry on the ow eld are studied by comparing controlled simulations at identical free stream conditions.