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Incident shock wave and supersonic turbulent boundarylayer interactions near an expansion corner

文献类型：期刊论文

作者Tong FL(童福林)2,3,4; Li XL(李新亮)1,4; Yuan XX2,3; Yu ZP(于长平)4
刊名COMPUTERS & FLUIDS
出版日期2020-02-15
卷号198页码:18
关键词Shock wave Turbulent boundary layer Unsteadiness Expansion corner
ISSN号0045-7930
DOI10.1016/j.compfluid.2019.104385
通讯作者Yu, Changping(cpyu@imech.ac.cn)
英文摘要Direct numerical simulations of incident shock wave and supersonic turbulent boundary layer interactions near an expansion corner are performed at Mach number M-infinity = 2.9 and Reynolds number Re-infinity = 5581 to investigate the expansion effect on the characteristic features of this phenomenon. Four expansion angles, i.e. alpha = 0(0) (flat-plate), 2(0), 5(0) and 10(0) are considered. The nominal impingement point of the oblique shock wave with a flow deflection angle of 12(0) is fixed at the onset of the expansion corner, and flow conditions are kept the same for all cases. The numerical results are in good agreement with previous experimental and numerical data. Various flow phenomena, including the flow separation, the post-shock turbulent boundary layer and the flow unsteadiness in the interaction region, have been systematically studied. Analysis of the instantaneous and mean flow fields indicates that the main effect of the expansion corner is to significantly decrease the size and three-dimensionality of the separation bubble. A modified scaling analysis is proposed for the expansion effect on the interaction length scale, and a satisfactory result is obtained. Distributions of the mean velocity, the Reynolds shear stress and the turbulent kinetic energy show that the post-shock turbulent boundary layer in the downstream region experiences a faster recovery to the equilibrium state as the expansion angle is increased. The flow unsteadiness is studied using spectral analysis and dynamic mode decomposition, and dynamically relevant modes associated with flow structures originated from the incoming turbulent boundary layer are clearly identified. At large expansion angle (alpha=10(0)), the unsteadiness of the separated shock is dominated by medium frequencies motions, and no low frequency unsteadiness is observed. The present study confirms that the driving mechanism of the low frequency unsteadiness is strongly related to the separated shock and the detached shear layer. (C) 2019 Elsevier Ltd. All rights reserved.
分类号二类
WOS关键词DIRECT NUMERICAL-SIMULATION ; WAVE/BOUNDARY-LAYER INTERACTION ; UNSTEADINESS ; FLOW
资助项目NSFC Projects[91852203] ; NSFC Projects[11972356] ; National Key Research and Development Program of China[2016YFA0401200] ; Science Challenge Project[TZ2016001] ; Strategic Priority Research Program of Chinese Academy of Sciences[XDA17030100]
WOS研究方向Computer Science ; Mechanics
语种英语
WOS记录号WOS:000514254000003
资助机构NSFC Projects ; National Key Research and Development Program of China ; Science Challenge Project ; Strategic Priority Research Program of Chinese Academy of Sciences
其他责任者Yu, Changping
源URL[http://dspace.imech.ac.cn/handle/311007/81568]  
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.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
2.China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang 621000, Sichuan, Peoples R China;
3.China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Sichuan, Peoples R China;
4.Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China;
推荐引用方式
GB/T 7714		 Tong FL,Li XL,Yuan XX,et al. Incident shock wave and supersonic turbulent boundarylayer interactions near an expansion corner[J]. COMPUTERS & FLUIDS,2020,198:18.
APA 童福林,李新亮,Yuan XX,&于长平.(2020).Incident shock wave and supersonic turbulent boundarylayer interactions near an expansion corner.COMPUTERS & FLUIDS,198,18.
MLA 童福林,et al."Incident shock wave and supersonic turbulent boundarylayer interactions near an expansion corner".COMPUTERS & FLUIDS 198(2020):18.

入库方式： OAI收割

来源：力学研究所

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