作　　者： ; ; ;

机构地区： 国防科学技术大学航天与材料工程学院宇航科学与工程系

出　　处： 《力学季刊》 2003年第3期287-291,共5页

摘　　要： 采用交替方向隐式分解的隐式NND格式求解全N-S方程模拟“类升力体”外形在高超声速下的大攻角流动,给出了“类升力体”外形表面极限流线随攻角变化的拓扑结构及40°攻角下垂直于体轴的横截面流线拓扑结构。结果表明:类升力体外形三维流场结构十分复杂,攻角从0°～40°变化时,背风面表面极限流线依次由不分离、开式分离向起始于鞍、结点组合的高阶奇点的分离方式转化,翼面横向分离亦随攻角增大而增大;垂直于体轴的横截面流动拓扑结构与文献[2]给出的理论分析一致。 The hypersonic flows of high attack angle over liftbody-type were simulated by solving N-S e-quations with alternating direction implicit NND scheme. The topological structures of hypersonic flow-field based on the limiting streamline of surface and sectional flow patterns perpendicular to the body axis were analyzed. The results show that with the angle of attack increasing from 0 to 40, the structure of limiting streamline of leeward surface changes from non-separating, open-separating to separating which occurs from the combined-point (which consists of saddle and nodal points). The separating area of upper wing surface increases with the angle of attack increasing. The topological structure based on the sectional flow patterns perpendicular to the body axis agrees well with the theory in paper [2].

关 键 词： 格式 升力体 方程 表面极限流线 拓扑分析

领　　域： [航空宇航科学与技术] [航空宇航科学技术]