Direct numerical simulations of hypersonic boundary layer transition over a hypersonic transition research vehicle model lifting body at different angles of attack

doi:10.1063/5.0146651

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

	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)
刊名	PHYSICS OF FLUIDS ; 4
	2023-04
卷号	35 页码:44111
ISSN号	1070-6631
DOI	10.1063/5.0146651
英文摘要	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.
分类号	一类/力学重要期刊
WOS研究方向	WOS:000972146700007
语种	英语
资助机构	National Key Research and Development Program of China [2019YFA0405300] ; NSFC [12232018, 12072349, 12202457]
其他责任者	Liu, HW
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/92260]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.(Men Hongyuan, Li Xinliang) Univ Chinese Acad Sci Sch Engn Sci Beijing 100049 Peoples R China 2.(Men Hongyuan, Li Xinliang, Liu Hongwei) Chinese Acad Sci Inst Mech LHD Beijing 100190 Peoples R China
推荐引用方式 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, 4,2023,35:44111.
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,35,44111.
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(2023):44111.