In hypersonic flows, the compressible effect becomes increasingly important for predicting drag and aero-heating. At high Mach numbers, the original turbulence models, such as the shear stress transport (SST) model, often overpredict the skin friction and aero-heating rate on the wall, and the spatial temperature distribution, while underpredicting the spatial turbulent kinetic energy (TKE). Meanwhile, the current compressibility corrections (CC) generally perform well for some flow variables but not for the others. For instance, the Danis and Durbin’s CC (2022) can predict temperature and velocity well but greatly underpredicts the spatial TKE. To accurately predict the skin friction, aero-heating rate, velocity, TKE and temperature, a new CC model based on SST model is proposed, combining the advantages of existing CC models, including the dilatation-dissipation and pressure-dilatation [1], viscous effects [2] and wall cooling [3]. This new CC model is validated by predicting the boundary layer flows past a flat plate with zero pressure gradient at Mach numbers ranging from 2.5 to 14. The spacial velocity, TKE and temperature from the original SST model, Danis and Durbin’s CC and the new CC were compared with the available DNS data. These comparisons show that the new CC model enhances the predictive capability for the drag and aero-heating.