The hypersonic compression corner flow was simulated by a fully coupled implicit method based on the shear stress transport (SST) turbulence model. Influence of seven factors including schemes

limiter functions and turbulence time steps

etc

on the robustness and convergence of calculation were evaluated. Results show that schemes and limiter functions have great influence on the convergence characteristic

and those with higher dissipation show better convergence characteristic of schemes and limiter functions. The increase of turbulent time step has little effect on convergence. The proper decrease of lower bound of turbulent variables can accelerate the convergence of turbulence equations substantially. Increase of Courant-Friedrichs-Lewy (CFL) number and inner iteration number of the lower-upper symmetric Gauss-Seidel (LU-SGS) method can accelerate the convergence greatly

while there are optimal values for different cases

the acceleration effect is not obvious if exceeding the optimal values.