Hypersonic shock wave and turbulent boundary layer interaction in a sharp cone/flare model
文献类型：期刊论文
| 作者 | Tong FL(童福林); Duan JY(段俊亦) ; Lai, Jiang4; Sun, Dong4; Yuan, Xianxu4
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| 刊名 | CHINESE JOURNAL OF AERONAUTICS
 |
| 出版日期 | 2023-03 |
| 卷号 | 36期号:3页码:80-95 |
| ISSN号 | 1000-9361 |
| 关键词 | Shock wave Hypersonic turbulent boundary layer Heat transfer Skin friction decomposition Direct numerical simulation |
| DOI | 10.1016/j.cja.2022.07.023 |
| 英文摘要 | A direct numerical simulation of hypersonic Shock wave and Turbulent Boundary Layer Interaction(STBLI) at Mach 6.0 on a sharp 7 degrees half angle circular cone/flare configuration at zero angle of attack is performed. The flare angle is 34 degrees and the momentum thickness Reynolds number based on the incoming turbulent boundary layer on the sharp circular cone is Reh = 2506. It is found that the mean flow is separated and the separation bubble occurring near the corner exhibits unsteadiness. The Reynolds analogy factor changes dramatically across the interaction, and varies between 1.06 and 1.27 in the downstream region, while the QP85 scaling factor has a nearly constant value of 0.5 across the interaction. The evolution of the reattached boundary layer is characterized in terms of the mean profiles, the Reynolds stress components, the anisotropy tensor and the turbulence kinetic energy. It is argued that the recovery is incomplete and the near wall asymptotic behavior does not occur for the hypersonic interaction. In addition, mean skin friction decomposition in an axisymmetric turbulent boundary layer is carried out for the first time. Downstream of the interaction, the contributions of transverse curvature and body divergence are negligible, whereas the positive contribution associated with the turbulence kinetic energy production and the negative spatial growth contribution are dominant. Based on scale decomposition, the positive contribution is further divided into terms with different spanwise length scales. The negative contribution is analyzed by comparing the convective term, the streamwise heterogeneity term and the pressure gradient term.(c) 2022 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY NC ND license (http://creativecommons.org/licenses/by nc nd/4.0/). |
| 分类号 | 一类 |
| WOS研究方向 | Engineering, Aerospace |
| 语种 | 英语 |
| WOS记录号 | WOS:000951064300001 |
| 资助机构 | National Natural Science Foundation of China [11972356, 91852203] ; National Key Research and Development Program of China [2019YFA0405300] |
| 其他责任者 | Yuan, XX (corresponding author), China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Peoples R China. ; Yuan, XX (corresponding author), China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang 621000, Peoples R China. |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/91848]  |
| 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 3.China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang 621000, Peoples R China 4.China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Peoples R China |
| 推荐引用方式 GB/T 7714 | Tong FL,Duan JY,Lai, Jiang,et al. Hypersonic shock wave and turbulent boundary layer interaction in a sharp cone/flare model[J]. CHINESE JOURNAL OF AERONAUTICS,2023,36(3):80-95. |
| APA | 童福林,段俊亦,Lai, Jiang,Sun, Dong,&Yuan, Xianxu.(2023).Hypersonic shock wave and turbulent boundary layer interaction in a sharp cone/flare model.CHINESE JOURNAL OF AERONAUTICS,36(3),80-95. |
| MLA | 童福林,et al."Hypersonic shock wave and turbulent boundary layer interaction in a sharp cone/flare model".CHINESE JOURNAL OF AERONAUTICS 36.3(2023):80-95. |
入库方式： OAI收割
来源：力学研究所
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