Numerical studies of shock wave interactions with a supersonic turbulent boundary layer in compression corner:Turning angle effects

doi:10.1016/j.compfluid.2017.03.009

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	Numerical studies of shock wave interactions with a supersonic turbulent boundary layer in compression corner:Turning angle effects
	Tong FL(童福林); Yu ZP(于长平); Tang ZG(唐志共); Li XL(李新亮); Li, XL (reprint author), Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China.; Li, XL (reprint author), Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China.
刊名	COMPUTERS & FLUIDS
	2017-06-13
卷号	149 页码:56-69
关键词	Compression Corner Low-frequency Oscillation Coherent Vortex Structure Power Spectrum Turbulent Kinetic Energy Budget Direct Numerical Simulation
ISSN号	0045-7930
DOI	10.1016/j.compfluid.2017.03.009
文献子类	Article
英文摘要	Direct numerical simulations (DNS) were performed to investigate the interactions of a Mach 2.9 turbulent boundary layer with shock waves of varying strengths in compression corner. The supersonic turbulent boundary layer was triggered by wall blowing-and-suction perturbations. The shock waves were produced by two-dimensional compression corners of 8, 14, 20 and 24 degrees. Compared with previous DNS results and experimental data, the numerical calculations were validated. The effects of shock wave on the boundary layer are studied by both flow visualizations and statistical analysis, and the results show that the intensity of fluctuations is amplified greatly by the shock wave. With the increasing of turning angle, three-dimensionality of separation bubble is significantly enhanced. Based on the statistics and power spectrum of the wall pressure signals, the effect of turning angle on the unsteadiness of shock motion is also studied, and the results show that the shock motions are quite different in the small and the large turning angle cases. The motion in the 8 and 14 cases is characterized by high-frequency and small amplitude, but the low-frequency and large-scale streamwise oscillation is the main feature in the 20 and 24 cases. The effect of turning angle on the turbulence state is analyzed by using the anisotropy of Reynolds stress tensor. The coherent vortex structures are also studied qualitatively. The results indicate that the cane-like streamwise vortexes in the near-wall region are the dominant structure for the small angle cases, while the hairpin vortexes and packets in the outer layer play the leading role in the large angle cases. According to the quantitative analysis of turbulent kinetic energy budgets in the separation region, the effect of turning angle on the transport mechanism is studied. It is found that the influence of shear layer above separation bubble on the mechanism is significant. (C) 2017 Elsevier Ltd. All rights reserved.
分类号	二类/Q1
WOS关键词	LARGE-EDDY SIMULATION ; RAMP INTERACTION ; SEPARATION ; UNSTEADINESS ; FLOWS
WOS研究方向	Computer Science ; Mechanics
语种	英语
WOS记录号	WOS:000400038700005
资助机构	Science Challenge Project(JCKY2016212A501) ; National Natural Science Foundation of China(91441103 ; (2016YFA0401200) ; 11372330 ; 11472278)
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/60906]
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	Li, XL (reprint author), Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China.; Li, XL (reprint author), Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China.
推荐引用方式 GB/T 7714	Tong FL,Yu ZP,Tang ZG,et al. Numerical studies of shock wave interactions with a supersonic turbulent boundary layer in compression corner:Turning angle effects[J]. COMPUTERS & FLUIDS,2017,149:56-69.
APA	童福林,于长平,唐志共,李新亮,Li, XL ,&Li, XL .(2017).Numerical studies of shock wave interactions with a supersonic turbulent boundary layer in compression corner:Turning angle effects.COMPUTERS & FLUIDS,149,56-69.
MLA	童福林,et al."Numerical studies of shock wave interactions with a supersonic turbulent boundary layer in compression corner:Turning angle effects".COMPUTERS & FLUIDS 149(2017):56-69.