Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study

doi:10.3390/aerospace11020148

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study
	Yu, Fangyou 1,2; Gao, Zhanbiao 2; Zhang, Qifan 2; Yue, Lianjie 1,2; Chen, Hao 2
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.