Numerical investigation of sideslip angle effects on swept-forward fin shock interactions
文献类型：期刊论文
| 作者 | Yang J(杨靖)1,2 ; Li GL(李广利)1,2; Chang SY(常思源)1; Tian ZW(田中伟)2,3; Xiao, Yao1,2; Cui K(崔凯)1,2
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| 刊名 | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING
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| 出版日期 | 2025-03-01 |
| 关键词 | Shock wave interactions hypersonic aerodynamic heat Computational Fluid Dynamics 3-D shock wave interactions |
| ISSN号 | 0954-4100 |
| DOI | 10.1177/09544100251328431 |
| 英文摘要 | The influence of sideslip angle on the 3-D asymmetry swept-forward fin shock interactions are analyzed by numerical simulation under Mach number 6.36, Reynolds number 3.27 x 107/m and wedge compression angle 12 degrees. Firstly, the effect of different swept-forward angles on the flow field structure and aerodynamic thermal characteristics under 0 degrees sideslip is analyzed. With the increase of the swept-forward angle, there are three kinds of shock wave interaction in turn on the symmetry plane: type IV interaction, the combination of type II and type III interaction, and type I interaction. Then, a typical swept-forward angle is selected for each interaction type, and the flow characteristics at 10 degrees and 20 degrees sideslip angles are simulated. The results indicate that: Under the influence of the sideslip, the heat distribution on the fin becomes asymmetric, and the maximum heat flux position at the fin's leading edge shifts from the symmetry plane to the windward side. The sideslip angle affects the maximum heat flux with changes within 10%. At all swept-forward angles, the windward heat flux increases significantly on the sidewall near the fin's leading edge as the sideslip angle increases. At a 20 degrees sideslip angle, for swept-forward angles of 20 degrees and 30 degrees, the maximum heat flux on the sidewall near the fin's leading edge exceeds the heat flux at the stagnation point of the two-dimensional cylinder with the same radius under free flow. For swept-forward angles of 45 degrees, the maximum heat flux on the sidewall near the leading edge is 0.74 times that of the two-dimensional cylindrical stagnation heat flux of the same radius under free flow. |
| 分类号 | Q3 |
| WOS研究方向 | Engineering, Aerospace ; Engineering, Mechanical ; Engineering |
| 语种 | 英语 |
| WOS记录号 | WOS:001449196500001 |
| 资助机构 | The author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: the Chinese Academy of Sciences Foundation Frontier Scientific Research Program (Grant No. ZDBS-LY-JSC005), 10.13039/501100001809 ; National Natural Science Foundation of China(No. 12002347). |
| 其他责任者 | 李广利 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/101451]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 宽域飞行工程科学与应用中心 |
| 作者单位 | 1.Chinese Academy of Sciences Inst Mechan; 2.University of Chinese Academy of Sciences, CAS; 3.Chinese Academy of Sciences Inst Mech |
| 推荐引用方式 GB/T 7714 | Yang J,Li GL,Chang SY,et al. Numerical investigation of sideslip angle effects on swept-forward fin shock interactions[J]. PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING,2025. |
| APA | 杨靖,李广利,常思源,田中伟,Xiao, Yao,&崔凯.(2025).Numerical investigation of sideslip angle effects on swept-forward fin shock interactions.PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING. |
| MLA | 杨靖,et al."Numerical investigation of sideslip angle effects on swept-forward fin shock interactions".PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING (2025). |
入库方式： OAI收割
来源：力学研究所
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