返回舱三维高超声速绕流及近尾迹流场数值模拟

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。

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

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 compa...