摘要
This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes Park＇s two temperature model and the air multi-species reaction model. The second-order accuracy TVD numerical method was deduced to compute the hypersonic aeroheating which improves the computational efficiency. Computational results are given to show the high accuracy comparing to the existing experimental data.
This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes Park＇s two temperature model and the air multi-species reaction model. The second-order accuracy TVD numerical method was deduced to compute the hypersonic aeroheating which improves the computational efficiency. Computational results are given to show the high accuracy comparing to the existing experimental data.
基金
supported by the National Natural Science Foundation of China(10872050)
the Fundamental Research Funds for the Centred Universities (DUT11ZD(G)01)
