高超声速流动粘性干扰效应研究  

Studies of hypersonic viscous interaction

作　　者：毛枚良[1] 万钊[1] 陈亮中[1] 陈坚强[1] 

机构地区：[1]中国空气动力研究与发展中心,空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2013年第2期137-143,共7页Acta Aerodynamica Sinica

摘　　要：基于边界层相似性理论,开展了高超声速流动粘性干扰效应的相关性分析,得到了粘性干扰造成的物面压力系数改变量与粘性干扰因子成正比的结论。通过对升力体简化外形的高超声速绕流流动的模拟,分析了粘性干扰效应对气动力/力矩的影响,计算结果表明:由粘性干扰导致的气动力系数的改变量与粘性干扰因子在特定范围内具有良好的线性关系。Based on the similarity solution for hypersonic boundary layers, correlative analyses for viscous interaction effect are conducted with numerical method, curves of the wall pressure on the surfaces of the ef- fective body vs the local effective angle of attack and the viscous interactive parameter are presented. The conclusion is that the difference between the wall pressure on the surfaces of the effective body and the real body is proportional to the viscous interactive parameter at bigger local effective angle of attack. Hypersonic flow fields around a lift-body configuration are numerically simulated, the numerical results validated the code and displayed the good agreement with the conclusion of correlative analyses.

关 键 词：高超声速流动 粘性干扰效应 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]