钝锥高超声速绕流空间分离形态的数值模拟及拓扑分析  

Numerical Simulation of Hypersonic Flows around Blunt Cones with Topological Analysis in Sectional Flow Patterns

作　　者：国义军[1] 宗文刚[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2000年第1期34-38,共5页Acta Aerodynamica Sinica

摘　　要：本文通过数值模拟和理论分析 ,系统研究了钝锥高超声速有迎角绕流时垂直于物面的截面流态沿轴向的演变过程。得出了高超声速情况下 ,背风分离区内的流态在大多数情况下貌似对称 ,其实是非对称的这一重要结论。考察了周向网格疏密程度对流动结构分辩率的影响 ,发现对分离流动的数值模拟 ,必须在分离区内布置足够密的网格才能给出正确的结果。In this paper,the hypersonic flows over blunt cones at angles of attack are simulated by solving NS equations.The numerical results are shown by drawing cross streamlines on the projected or sectional planes perpendicular to the body surface.The topological structure as well as its evolution along the axial direction of this kind of flow pattern is investigated theoretically.An important conclusion is drawn from this study.We find that the flow patterns,even on hypersonic conditions,maybe unsymmetrical whenever the flow is separated.Although the patterns look like symmetrical,but they are unsymmetrical actually.We also find that the numbers of grids distributed along circular direction has great influence on the numerical results of topological structure.

关 键 词：分离流动 拓扑分析 结构稳定性 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]