摘要
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。
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.
出处
《空气动力学学报》
CSCD
北大核心
1996年第2期162-167,共6页
Acta Aerodynamica Sinica
关键词
高超声速流
NND格式
欧拉方程
数值模拟
hypersonic flow, NND scheme, Euler equation, numericalsimulation.
