【摘要】 文章基于Euler方程及N_S方程的数值求解方法 ,对返回舱亚、跨声速和高超声速的流场及气动特性进行了数值模拟 ,其中Euler方程数值求解采用二阶Godunov有限体积法 ;N_S方程数值求解采用二阶Harten_Yee格式的差分法。得到同实验值一致的物面压力、气动力系数和在不同速度范围出现的激波、流动分离及旋涡等流场特征。通过完全气体、平衡气体和非平衡气体的流场数值模拟结果分析比较 ,得出真实气体效应对返回舱气动力特性影响较小这一结论。计算结果表明数值模拟方法是预测返回舱气动特性的有效手段更多还原

【Abstract】 A numerical simulation of sub_tranconic and hypersonic flow fields over recovery capsule is studied by solving Euler equations and Navier_Stokes qeuations. The Euler equations are solved by Second Order Godunov Limited Volume Method. Harten_Yee/TVD scheme is applied to solve the Navier_Stokes equations. The surface pressure distributions, aerodynamic coefficients, flow features including shock wave, flow separation and vortex are obtained by using above numerical procedure for capsule in different range of speed. Moreover, the numerical results agree well with those of experiments. Through analyses for the numerical results of flow_field of perfect air, equilibrium and Non_Equilibrium air, this thesis demonstrates that the influence of real air effects on the aerodynamics characters of the capsule is not significant. The numerical results illustrated that the numerical simulation is an effective tool to predict aerodynmic characters capsule.更多还原