Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25

doi:10.1016/j.cja.2023.06.015

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

	Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25
	Duan, Junyi 2,3; Tong, Fulin 1; Li, Xinliang 2,3; Liu, Hongwei 3
刊名	CHINESE JOURNAL OF AERONAUTICS
	2023-09-01
卷号	36 期号:9 页码:178-194
关键词	Compressible flow Boundary layers Direct numerical simulation Shock waves Skin friction Turbulent flow
ISSN号	1000-9361
DOI	10.1016/j.cja.2023.06.015
通讯作者	Liu, Hongwei(hliu@imech.ac.cn)
英文摘要	The evolution characteristics of the mean skin friction beneath the supersonic turbulent boundary layer that interacts with incident shock waves at Mach 2.25 are analyzed using Direct Numerical Simulation (DNS). The separated and attached boundary layers in the interaction region that respectively correspond to 33.2 degrees and 28 degrees incident shock angles are considered. The mean skin friction recovery rate for the separated boundary layer is much gentler and distinctly less than that for the attached case where the skin friction completes its recovery within one boundary layer thick-ness. The novel mean skin friction decomposition method for compressible flows proposed by the recent research is applied in the interaction region to investigate the internal evolution characteristics quantitatively. The results reveal that the three decomposition components are distinctly unequal between the two cases. The contributions of the turbulent motions at different scales to the associated term are focused on using empirical mode decomposition technology. It indicates that the outer large-scale structures dominate separation and reattachment regions, while contributions from inner small-scale structures are limited. In contrast, contributions from the outer large-scale structures are dramatically reduced in the attached case, which results in the outer large-scale and inner small-scale motions being of equal importance.(c) 2023 Production and hosting by Elsevier Ltd. on behalf of Chinese Society of Aeronautics and Astronautics. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/ licenses/by-nc-nd/4.0/).
WOS关键词	DIRECT NUMERICAL-SIMULATION ; WAVE STRUCTURE ; UNSTEADINESS
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:001084134400001
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/93150]
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	Liu, Hongwei
作者单位	1.China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Peoples R China 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 3.Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Duan, Junyi,Tong, Fulin,Li, Xinliang,et al. Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25[J]. CHINESE JOURNAL OF AERONAUTICS,2023,36(9):178-194.
APA	Duan, Junyi,Tong, Fulin,Li, Xinliang,&Liu, Hongwei.(2023).Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25.CHINESE JOURNAL OF AERONAUTICS,36(9),178-194.
MLA	Duan, Junyi,et al."Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25".CHINESE JOURNAL OF AERONAUTICS 36.9(2023):178-194.