Simulation of flow field in a supersonic inlet by γ-Re_θ turbulence model

To improve the prediction of transition, the γ-Re_θ turbulence model involved with empirical correlations for transition prediction is used to analyze two typical hypersonic flow fields of the blunt cone and the flat plat shock wave/boundary layer interaction, and the computational results agree well with the experimental results, which show that the turbulence transition model adopted in this paper has a higher credibility than traditional turbulence models. Furthermore, two supersonic inlets with triple-compression angle and isentropic compression profile are designed and simulated, respectively. The results show that the isentropic compression profile has better throat flow capability and higher total pressure recovery performance and the aerodynamic performances at the rear part of the throat section are almost the same for the two cases.