| Large eddy simulation of a hypersonic turbulent boundary layer over a compression corner | |
Qi H(齐涵); Li XL(李新亮) ; Ji, Xiangxin1; Tong FL(童福林); Yu ZP(于长平)
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| Source Publication | AIP ADVANCES
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| 2023-02-01 | |
| Volume | 13Issue:2Pages:25265 |
| Abstract | 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/). |
| DOI | 10.1063/5.0139966 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000939763700004 |
| WOS Research Area | Nanoscience & Nanotechnology ; Materials Science, Multidisciplinary ; Physics, Applied |
| WOS Subject | Science & Technology Other Topics ; Materials Science ; Physics |
| Funding Organization | 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] |
| Classification | Q3 |
| Ranking | 1 |
| Contributor | Yu, CP (corresponding author), Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China. |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/91779 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 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 3.Computat Aerodynam Inst China Aerodynam Res, Dev Ctr, Mianyang 621000, Sichuan, Peoples R China |
| Recommended Citation 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.Rp_Au:Yu, CP (corresponding author), Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China. |
| 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. |
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| Jp2023A188.pdf（7382KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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