Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study | |
Yu, Fangyou1,2; Gao, Zhanbiao2; Zhang, Qifan2; Yue, Lianjie1,2; Chen, Hao2 | |
刊名 | AEROSPACE |
2024-02-01 | |
卷号 | 11期号:2页码:16 |
关键词 | micro-serration separation control shock wave/boundary layer interaction |
DOI | 10.3390/aerospace11020148 |
通讯作者 | Zhang, Qifan(zhangqifan@imech.ac.cn) ; Chen, Hao(chenhao@imech.ac.cn) |
英文摘要 | Suppressing shock-induced flow separation has been a long-standing problem in the design of supersonic vehicles. To reduce the structural and design complexity of control devices, a passive control technique based on micro-serrations is proposed and its controlling effects are preliminarily investigated under test conditions in which the Mach number is 2.5 and the ramp creating an incident shock is 15 deg. Meanwhile, a vorticity-based criterion for assessing separation scales is developed to resolve the inapplicability of the zero skin friction criterion caused by wall unevenness. The simulations demonstrate that the height of the first stair significantly influences the separation length. Generally, the separation length is shorter at higher stairs, but when the height is greater than half of the thickness of the incoming boundary layer, the corresponding separation point moves upstream. A stair with a height of only 0.4 times the thickness of the boundary layer reduces the separation length by 2.69%. Further parametric analysis reveals that while the remaining serrations have limited effects on the flow separation, an optimization of their shape (depth and width) can create more favorable spanwise vortices and offer a modest improvement of the overall controlling performance. Compared to the plate case, a 9.13% reduction in the separation length can be achieved using a slightly serrated design in which the leading stair is 0.1 high and the subsequent serrations are 0.2 deep and 0.05 wide (nondimensionalized, with the thickness of the incoming boundary layer). Meanwhile, the micro-serration structure even brings less drag. Considering the minor modification to the structure, the proposed method has the potential for use in conjunction with other techniques to exert enhanced control on separations. |
资助项目 | National Natural Science Foundation of China |
WOS关键词 | LARGE-EDDY SIMULATION ; BOUNDARY-LAYER INTERACTION ; VORTEX GENERATORS ; FLOW ; TRANSITION |
WOS研究方向 | Engineering |
语种 | 英语 |
WOS记录号 | WOS:001172243800001 |
资助机构 | National Natural Science Foundation of China |
内容类型 | 期刊论文 |
源URL | [http://dspace.imech.ac.cn/handle/311007/94978] |
专题 | 力学研究所_高温气体动力学国家重点实验室 |
通讯作者 | Zhang, Qifan; Chen, Hao |
作者单位 | 1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China |
推荐引用方式 GB/T 7714 | Yu, Fangyou,Gao, Zhanbiao,Zhang, Qifan,et al. Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study[J]. AEROSPACE,2024,11(2):16. |
APA | Yu, Fangyou,Gao, Zhanbiao,Zhang, Qifan,Yue, Lianjie,&Chen, Hao.(2024).Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study.AEROSPACE,11(2),16. |
MLA | Yu, Fangyou,et al."Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study".AEROSPACE 11.2(2024):16. |
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