| Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack | |
Men, Hongyuan; Li XL(李新亮) ; Liu HW(刘洪伟)
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| Source Publication | PHYSICS OF FLUIDS
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| 2023-04 | |
| Volume | 35Issue:4Pages:44111 |
| ISSN | 1070-6631 |
| Abstract | This paper performs direct numerical simulations of hypersonic boundary layer transition over a Hypersonic Transition Research Vehicle (HyTRV) model lifting body designed by the China Aerodynamic Research and Development Center. Transitions are simulated at four angles of attack: 0 degrees, 3 degrees, 5 degrees, and 7 degrees. The free-stream Mach number is 6, and the unit Reynolds number is 10(7) m(-1). Four distinct transitional regions are identified: the shoulder cross-flow and vortex region and the shoulder vortex region on the leeward side, the windward vortex region and the windward cross-flow region on the windward side. As the angle of attack increases, the transition locations on the leeward side generally move forward and the transition ranges expand, while the transition locations generally move backward and the transition ranges decrease on the windward side. Moreover, the shoulder vortex region moves toward the centerline of the leeward side. At large angles of attack (5 degrees and 7 degrees), the streamwise vortex on the shoulder cross-flow and vortex region will enable the transition region to be divided into the cross-flow instability region on both sides and the streamwise vortex instability region in the middle. In addition, the streamwise vortex also leads to a significant increase in cross-flow instability in their upper region, which can generate a new streamwise vortex instability region between the two transition regions on the leeward side. Furthermore, since the decrease in the intensity and the range for the cross flow on the windward side, the windward cross-flow region tends to become narrow and ultimately disappears. |
| DOI | 10.1063/5.0146651 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000972146700007 |
| Funding Organization | National Key Research and Development Program of China [2019YFA0405300] ; NSFC [12232018, 12072349, 12202457] |
| Classification | 一类/力学重要期刊 |
| Ranking | 1 |
| Contributor | Liu, HW |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/92260 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.(Men Hongyuan, Li Xinliang, Liu Hongwei) Chinese Acad Sci Inst Mech LHD Beijing 100190 Peoples R China 2.(Men Hongyuan, Li Xinliang) Univ Chinese Acad Sci Sch Engn Sci Beijing 100049 Peoples R China |
| Recommended Citation GB/T 7714 | Men, Hongyuan,Li XL,Liu HW. Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack[J]. PHYSICS OF FLUIDS,2023,35,4,:44111.Rp_Au:Liu, HW |
| APA | Men, Hongyuan,李新亮,&刘洪伟.(2023).Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack.PHYSICS OF FLUIDS,35(4),44111. |
| MLA | Men, Hongyuan,et al."Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack".PHYSICS OF FLUIDS 35.4(2023):44111. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| Jp2023A060.pdf（13263KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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