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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。
Computational fluid dynamics (CFD) method was used to study the aerodynamic heat numerical simulation of hypersonic vehicles. The grid dependence of aerodynamic thermal environment under hypersonic velocity was studied. Taking the two-dimensional cylinder as an example, the influence of grid Reynolds number on heat flow calculation is analyzed, and the effect of grid Reynolds number and local grid encryption on heat flow accuracy is obtained. The results show that the convergence heat flow can be obtained when the Reynolds number of the grid is less than 8, and the grid encryption at the shock location can effectively improve the heat flow prediction accuracy. The applicability of the research findings in the 3D model was tested by the aerodynamic thermal simulation of the X-33 reentry vehicle.