Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack
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Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack
Vol. 26, Issue 12, (2011)
作者机构:
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
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Published:2011
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YUAN Xiang-jiang, LI Guo-liang, LIU Zhi-yong, et al. Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack[J]. 2011, 26(12).
DOI:
YUAN Xiang-jiang, LI Guo-liang, LIU Zhi-yong, et al. Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack[J]. 2011, 26(12).DOI:
Study of the instability characteristic in the boundary layer of a hypersonic blunt cone at low angle of attack
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.