Direct numerical simulation of hypersonic boundary layer transition over a lifting body at different angles of sideslip
文献类型：期刊论文
| 作者 | Yang LY(杨凌云)1,2; Li XL(李新亮)1,2; Liu HW(刘洪伟)1 |
| 刊名 | PHYSICS OF FLUIDS
 |
| 出版日期 | 2025-03-01 |
| 卷号 | 37期号:3页码:18 |
| ISSN号 | 1070-6631 |
| DOI | 10.1063/5.0258378 |
| 通讯作者 | Liu, Hongwei(hliu@imech.ac.cn) |
| 英文摘要 | Hypersonic boundary layer transition on a hypersonic transition research vehicle model lifting body by direct numerical simulations under typical hypersonic conditions is investigated. The simulations analyze the model at three angles of sideslip: 0 degrees, 2 degrees, and 4 degrees. The freestream Mach number is 6, the unit Reynolds number is 1x10(-7)m(-1), with a fixed 2 degrees angle of attack. The result indicates that asymmetric transition occurs on the lifting body's surface between the sideslip windward and leeward sides, due to the side incoming flow. Five distinct transition regions are identified: the shoulder crossflow-vortex region, the shoulder vortex region, the lower surface vortex region, the lower surface crossflow region, and the top crossflow-vortex region. The shoulder crossflow-vortex region (windward) shows forward-shifting transition and expanding ranges as the angle of sideslip increases, with two different modes in the head of transition. The transition of the shoulder vortex region (leeward) moves forward and shifts spanwisely toward the attachment line; at the angle of sideslip of 4 degrees, the transition mode induced by the secondary instability of the stationary crossflow occurs. In the lower surface vortex region, transition moves forward, accompanied by localized turbulence spots and altered disturbance patterns at the high angle of sideslip. The lower surface crossflow-vortex (windward) region exhibits a transition region including two zones, while lower surface crossflow-vortex region (leeward) dissipates. The top crossflow-vortex region experiences intensified crossflow effects and localized turbulence spots as the angle of sideslip increases, with the appearance of the distinct topline similar to the attachment line. |
| 分类号 | 一类/力学重要期刊 |
| WOS关键词 | CROSS-FLOW VORTICES ; SECONDARY INSTABILITY |
| 资助项目 | National Natural Science Foundation of China10.13039/501100001809[12232018] ; National Natural Science Foundation of China10.13039/501100001809[12072349] ; National Natural Science Foundation of China10.13039/501100001809[12202457] ; National Natural Science Foundation of China[XDB0620203] ; Strategic Priority Research Program of Chinese Academy of Sciences |
| WOS研究方向 | Mechanics ; Physics |
| 语种 | 英语 |
| WOS记录号 | WOS:001447603100021 |
| 资助机构 | National Natural Science Foundation of China10.13039/501100001809 ; National Natural Science Foundation of China ; Strategic Priority Research Program of Chinese Academy of Sciences |
| 其他责任者 | 刘洪伟 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/100706]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 作者单位 | 1.Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China |
| 推荐引用方式 GB/T 7714 | Yang LY,Li XL,Liu HW. Direct numerical simulation of hypersonic boundary layer transition over a lifting body at different angles of sideslip[J]. PHYSICS OF FLUIDS,2025,37(3):18. |
| APA | 杨凌云,李新亮,&刘洪伟.(2025).Direct numerical simulation of hypersonic boundary layer transition over a lifting body at different angles of sideslip.PHYSICS OF FLUIDS,37(3),18. |
| MLA | 杨凌云,et al."Direct numerical simulation of hypersonic boundary layer transition over a lifting body at different angles of sideslip".PHYSICS OF FLUIDS 37.3(2025):18. |
入库方式： OAI收割
来源：力学研究所
浏览0
下载0
收藏0
其他版本
除非特别说明，本系统中所有内容都受版权保护，并保留所有权利。