高超声速飞行器气动热网格依赖性研究

Investigation of the Grid-dependency in Heat Transfer Simulation for Hypersonic Vehicle

采用计算流体力学方法,针对高超声速飞行器气动热数值模拟问题,研究了高超声速来流下气动热环境计算的网格依赖性。以二维圆柱为例,分析了网格雷诺数对热流计算的影响,获得了网格雷诺数及网格局部加密对热流精度的影响规律。研究结果表明,网格雷诺数小于8即可获得收敛的热流结果,激波位置处网格加密可有效改善热流预测精度。通过对X-33再入飞行器的气动热环境模拟检验了研究结论在三维模型中的适用性。

For the numerical simulation of the hypersonic vehicle aerothermal heating, the grid-depend- ency of the aerothermal computation under the hypersonic flow was studied by the means of computational fluid dynamic. By employing two-dimensional cylinder model, the influence of the grid-reynolds number to heat transfer simulation was researched, and the connection between grid refinement in the position of shock wave and the heat transfer computational accuracy was established. The result indicates that the grid-reynolds number less than 8 can gain a convergent result of heat transfer and the grid refinement in the position of shock wave was beneficial for the heat transfer simulation. Besides, the applicability of the gird criterion to the computation of three-dimensional model was verified by the aerothermal simulation of the X-33 hypersonic vehicle.