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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角下背风面流场的技术，大量计算表明，结果准确、可靠。气动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。
In this paper, NND difference scheme is used to simulate the high angle of inertial flow with no-viscous flow around mid-angle of attack of a maneuverable vehicle by the method of propulsion-iteration. A technique suitable for dealing with the flow field of leeward surface at medium angle of attack is developed. Show that the results are accurate and reliable. The aerodynamic coefficient and wall pressure distribution are consistent with the experimental data, and the wave structure of the flow field is simulated correctly.