Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6

doi:10.1063/5.0118578

	Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6
	Zhang J(张继)1,2; Guo TB(郭同彪)1; Dang GL(党冠麟)1,2; Li XL(李新亮)1,2
通讯作者	Li, Xinliang(lixl@imech.ac.cn)
发表期刊	PHYSICS OF FLUIDS
	2022-11-01
卷号	34 期号:11 页码:15
ISSN	1070-6631
摘要	Swept compression ramps widely exist in supersonic/hypersonic vehicles and have become a typical standard model for studying three-dimensional (3D) shock wave/turbulent boundary layer interactions (STBLIs). In this paper, we conduct a direct numerical simulation of swept compression ramp STBLI with a 34 degrees compression angle and a 45 degrees sweep angle at Mach 6 using a heterogeneous parallel finite difference solver. Benefitting from the powerful computing performance of the graphics processing unit, the computational grid number exceeds 5 x 10(6) with the spatiotemporal evolution data of hypersonic 3D STBLI obtained. The results show that the flow of the hypersonic swept compression ramp follows the quasi-conical symmetry. A supersonic crossflow with helical motion appears in the interaction region, and its velocity increases along the spanwise direction. Fluids from the high-energy-density region pass through the bow shock at the head of the main shock and crash into the wall downstream of the reattachment, resulting in the peaks in skin friction and heat flux. The peak friction and heating increase along the spanwise direction because of the spanwise variation in the shock wave inclination. In the interaction region, the unsteadiness is dominated by the mid-frequency motion, whereas the low-frequency large-scale motion is nearly absent. Two reasons for the lack of low-frequency unsteadiness are given: (1) The separation shock is significantly weaker than the reattachment shock and main shock; and (2) because of the supersonic crossflow, the perturbations propagating at the sound speed are not self-sustaining but flow along the r-direction and toward the spanwise boundary. Published under an exclusive license by AIP Publishing.
DOI	10.1063/5.0118578
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000880314400011
关键词[WOS]	LOW-FREQUENCY UNSTEADINESS ; FLOW ; SIMILARITY
WOS研究方向	Mechanics ; Physics
WOS类目	Mechanics ; Physics, Fluids & Plasmas
资助项目	National Key Research and Development Program of China ; National Natural Science Foundation of China ; [2019YFA0405300] ; [12232018] ; [91852203] ; [12072349] ; [12202457] ; [202202015832]
项目资助者	National Key Research and Development Program of China ; National Natural Science Foundation of China
论文分区	一类/力学重要期刊
力学所作者排名	1
RpAuthor	Li, Xinliang
引用统计	被引频次：6[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/90778
专题	高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
推荐引用方式 GB/T 7714	Zhang J,Guo TB,Dang GL,et al. Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6[J]. PHYSICS OF FLUIDS,2022,34,11,:15.
APA	张继,郭同彪,党冠麟,&李新亮.(2022).Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6.PHYSICS OF FLUIDS,34(11),15.
MLA	张继,et al."Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6".PHYSICS OF FLUIDS 34.11(2022):15.

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