| Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study | |
Yu FY(于方游)1,2; Gao ZB(高占彪)1 ; Zhang QF(张启帆)1; Yue LJ(岳连捷)1,2; Chen H(陈昊)1
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| Corresponding Author | Zhang, Qifan([email protected]) ; Chen, Hao([email protected]) |
| Source Publication | AEROSPACE
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| 2024-02-01 | |
| Volume | 11Issue:2Pages:16 |
| Abstract | 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. |
| Keyword | micro-serration separation control shock wave/boundary layer interaction |
| DOI | 10.3390/aerospace11020148 |
| Indexed By | SCI |
| Language | 英语 |
| WOS ID | WOS:001172243800001 |
| WOS Keyword | LARGE-EDDY SIMULATION ; BOUNDARY-LAYER INTERACTION ; VORTEX GENERATORS ; FLOW ; TRANSITION |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Natural Science Foundation of China |
| Funding Organization | National Natural Science Foundation of China |
| Classification | 二类 |
| Ranking | 1 |
| Contributor | Zhang, Qifan ; Chen, Hao |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/94979 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China |
| Recommended Citation GB/T 7714 | Yu FY,Gao ZB,Zhang QF,et al. Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study[J]. AEROSPACE,2024,11,2,:16.Rp_Au:Zhang, Qifan, Chen, Hao |
| APA | 于方游,高占彪,张启帆,岳连捷,&陈昊.(2024).Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study.AEROSPACE,11(2),16. |
| MLA | 于方游,et al."Mitigation of Shock-Induced Separation Using Square-Shaped Micro-Serrations-A Preliminary Study".AEROSPACE 11.2(2024):16. |
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