机动飞行器中等攻角高超声速无粘绕流数值模拟

本文采用ＮＮＤ差分格式，利用推进－迭代方法，数值模拟了机动飞行器的中等攻角高超声速无粘绕流流场，发展了一种适用于处理中等攻下背风面流场的技术，大量计算表明，结果准确、可靠。气动力力系数和壁面压力分布与实验数据一致，流场波系结构模拟正确。

Numerical Simulation of Hypersonic Inviscid Flow at Intermediate Angle of Attack over a Maneuver Vehicle

Hypersonic inviscid flowfields at intermediate angle of attack about a maneuyer missile are simulated by a spacial-marching and iteration algorithm with NND scheme deyeloppd by professor Zhang Hanxin.A special technique to deal with the leeward flowfields at intermediate angle of attack is developed in this paper. A great deal of numerical results show that the computational results are correct and reliable. It is shown that the aeroxdynamics coefficients and the pressure distributions are well consisted with experimental data,and the structures of shock kaye in the flowfields are correctly simulated.