Large eddy simulation of a hypersonic turbulent boundary layer over a compression corner
文献类型：期刊论文
| 作者 | Qi H(齐涵); Li XL(李新亮) ; Ji, Xiangxin1; Tong FL(童福林); Yu ZP(于长平)
|
| 刊名 | AIP ADVANCES
 |
| 出版日期 | 2023-02-01 |
| 卷号 | 13期号:2页码:25265 |
| DOI | 10.1063/5.0139966 |
| 英文摘要 | In this paper, large eddy simulation of the interaction between a shock wave and the hypersonic turbulent boundary layer in a compression corner with a fixed 34 degrees deflection angle at Ma = 6 for different Reynolds number cases is conducted. For investigating the effects of the Reynolds number for hypersonic cases, three cases where the free stream Reynolds numbers are 14000, 20000, and 30000/mm are selected. The averaged statistics, such as the mean velocity, the skin friction, the heat flux, and the wall pressure, are used in this paper. The flow structures in the compression ramp including the shock wave and interaction region are discussed. The decomposition of the mean skin friction drag for the flat flow is extended to be used in the compression corner. In addition, the turbulent kinetic energy is studied through the decomposition of the mean skin friction drag for the flat plate region and the corner region. It is found that higher Reynolds numbers would increase the turbulent kinetic energy by turbulent dissipation at the interaction region, while higher Reynolds numbers would decrease the turbulent kinetic energy by turbulent dissipation after reattachment. In addition, it is also found that the turbulent kinetic energy is larger with a higher Reynolds number and higher turbulent kinetic energy inhibits the movement from the separation point to the inflection point (x = 0 mm), which deduces larger separation bubbles. (c) 2023 Author(s). All article content, except where otherwise noted, is licensed under a Creative Commons Attribution (CC BY) license (http://creativecommons.org/licenses/by/4.0/). |
| 分类号 | Q3 |
| WOS研究方向 | Nanoscience & Nanotechnology ; Materials Science, Multidisciplinary ; Physics, Applied |
| 语种 | 英语 |
| WOS记录号 | WOS:000939763700004 |
| 资助机构 | National Key Research and Development Program of China [2020YFA0711800, 2019YFA0405302] ; NSFC Projects [12072349, 91852203, 12202457] ; National Numerical Windtunnel Project ; Science Challenge Project [TZ2016001] ; Strategic Priority Research Program of Chinese Academy of Sciences [XDC01000000] |
| 其他责任者 | Yu, CP (corresponding author), Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China. |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/91779]  |
| 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.Computat Aerodynam Inst China Aerodynam Res, Dev Ctr, Mianyang 621000, Sichuan, Peoples R China 3.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China |
| 推荐引用方式 GB/T 7714 | Qi H,Li XL,Ji, Xiangxin,et al. Large eddy simulation of a hypersonic turbulent boundary layer over a compression corner[J]. AIP ADVANCES,2023,13(2):25265. |
| APA | 齐涵,李新亮,Ji, Xiangxin,童福林,&于长平.(2023).Large eddy simulation of a hypersonic turbulent boundary layer over a compression corner.AIP ADVANCES,13(2),25265. |
| MLA | 齐涵,et al."Large eddy simulation of a hypersonic turbulent boundary layer over a compression corner".AIP ADVANCES 13.2(2023):25265. |
入库方式： OAI收割
来源：力学研究所
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