返回舱三维高超声速绕流及近尾迹流场数值模拟

NUMERICAL SIMULATION OF 3-D HYPEKSONIC FLOW AND NEAR WAKE AROUND BE-ENTBY VEHICLE

为使返回舱安全、稳定、可靠地飞行，准确地计算其周围的复杂绕流流场，对飞船的初步设计是十分必要的。用Ｈａｒｔｅｎ－Ｙｅｅ的二阶迎风ＴＶＤ有限差分格式求解薄层Ｎ－Ｓ方程，模拟了返回舱三维高超声速流场，Ｍ＿∞＝７．３５，Ｒｅ＿∞＝７．５×１０￣５，α＝１０°、２０°。给出了详细的绕流结构，不同攻角、不同子午面上的物面压力分布与Ｍｏｓｅｌｅｙ和ｗｅｌｌｓ的实验数据进行了比较，符合较好。通过分析表明，在一定的攻角下，倒锥体上低压区压力的计算精度，对力矩系数及压心位置仍有明显的影响。

The knowledge of complex three-dimehsional hypersonic visous flow over re-entry bodies is of great importance in the preliminary design of atmospheric re-entry vehicles.The thin-layer Navier-Stokes equations are solved with Harte-Yee's second-order TVD fiuitedifference scheme for three-dimensional hypersonic flowfields over a re-entry vehicle, whereM_∞ =7.35,Re_∞=7.5×10￣5,α=10°,20°。The detailed flowfield structures are given.The pressure distributions along body surface at various angles of attack are compared withexperimental data and good argeements are obtained. Further analyses show that,at acertain angle of attack, computed pressure accuracy for low pressure region over afterbodygreatly affects the vehicle's moment coefficient and the center of pressure.