小攻角高超声速钝锥边界层失稳特性

袁湘江; 李国良; 刘智勇; 涂国华

小攻角高超声速钝锥边界层失稳特性

1.
中国航天空气动力技术研究院第一研究所, 北京 100074
2.
中国空气动力研究与发展中心国家计算流体力学实验室, 北京 100191

基金项目: 国家自然科学基金(10872018)

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出版历程
- 收稿日期: 2011-01-31
- 修回日期: 2011-06-29
- 刊出日期: 2011-12-28

Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack

1.
The 1st Institute, China Academe of Aerospace Aerodynamics, Beijing 100074, China
2.
National Computational Fluid Dynamics Laboratory, China Aerodynamics Research and Development Center, Beijing 100191, China

摘要

摘要: 利用高阶紧致格式,采用直接数值模拟(DNS)和线性稳定性(LST)分析方法,对高超声速边界层的失稳机制和转捩特点进行了研究.通过对马赫数为6的2?攻角高超声速钝锥边界层的稳定性分析发现:小攻角高超声速钝锥边界层存在多枝不稳定模态;周向速度使钝锥的稳定性特征与不考虑周向速度时有本质的差别;转捩线在接近背风面处出现拐折现象是由失稳模态发生转换引起的.
- 高超声速 /
- 攻角 /
- 钝锥 /
- 边界层 /
- 失稳特性
Abstract: DNS(direct numerical simulation) and LST(linear stability theory) were employed as tools to study the characteristics of instabilities and transitions in hypersonic boundary layers.The characteristics for flow past a blunt cone in Mach 6 free-stream with 5 half-angle at 2 degree angle of attack (AOA) were analyzed.The results show that there are multi branch instability modes.The instabilities of the blunt cone with the crossflow generated due to AOA is essential different from the cases without the crossflow.The crook in the transition front near the leeward line arises from a transformation between the instability modes.
- hypersonic /
- angle of attack /
- blunt cone /
- boundary layer /
- instability characteristic

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参考文献(12)

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