Aerothermal characteristics of bleed slot in hypersonic flows

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	Aerothermal characteristics of bleed slot in hypersonic flows
	Yue LJ(岳连捷); Lu HB; Xu X; Chang XY
刊名	SCIENCE CHINA-PHYSICS MECHANICS & ASTRONOMY
	2015-10
通讯作者邮箱	yuelj@imech.ac.cn
卷号	58 期号:10 页码:104703
关键词	boundary layer control boundary layer heat flow shock wave interactions separated flows
ISSN号	1674-7348
通讯作者	Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China.
产权排序	[Yue LianJie; Lu HongBo; Xu Xiao; Chang XinYu] Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
中文摘要	Two types of flow configurations with bleed in two-dimensional hypersonic flows are numerically examined to investigate their aerodynamic thermal loads and related flow structures at choked conditions. One is a turbulent boundary layer flow without shock impingement where the effects of the slot angle are discussed, and the other is shock wave boundary layer interactions where the effects of slot angle and slot location relative to shock impingement point are surveyed. A key separation is induced by bleed barrier shock on the upstream slot wall, resulting in a localized maximum heat flux at the reattachment point. For slanted slots, the dominating flow patterns are not much affected by the change in slot angle, but vary dramatically with slot location relative to the shock impingement point. Different flow structures are found in the case of normal slot, such as a flow pattern similar to typical Laval nozzle flow, the largest separation bubble which is almost independent of the shock position. Its larger detached distance results in 20% lower stagnation heat flux on the downstream slot corner, but with much wider area suffering from severe thermal loads. In spite of the complexity of the flow patterns, it is clearly revealed that the heat flux generally rises with the slot location moving downstream, and an increase in slot angle from 20 to 40 reduces 50% the heat flux peak at the reattachment point in the slot passage. The results further indicate that the bleed does not raise the heat flux around the slot for all cases except for the area around the downstream slot corner. Among all bleed configurations, the slot angle of 40 located slightly upstream of the incident shock is regarded as the best.
分类号	二类/Q3
类目[WOS]	Physics, Multidisciplinary
研究领域[WOS]	Physics
关键词[WOS]	BOUNDARY-LAYER INTERACTIONS ; SHOCK ; INLETS ; SEPARATION ; SUCTION ; MACH-6
收录类别	SCI ; EI ; CSCD
原文出处	http://dx.doi.org/10.1007/s11433-015-5698-z
语种	英语
WOS记录号	WOS:000361783300007
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/58418]
专题	力学研究所_高温气体动力学国家重点实验室
推荐引用方式 GB/T 7714	Yue LJ,Lu HB,Xu X,et al. Aerothermal characteristics of bleed slot in hypersonic flows[J]. SCIENCE CHINA-PHYSICS MECHANICS & ASTRONOMY,2015,58(10):104703.
APA	岳连捷,Lu HB,Xu X,&Chang XY.(2015).Aerothermal characteristics of bleed slot in hypersonic flows.SCIENCE CHINA-PHYSICS MECHANICS & ASTRONOMY,58(10),104703.
MLA	岳连捷,et al."Aerothermal characteristics of bleed slot in hypersonic flows".SCIENCE CHINA-PHYSICS MECHANICS & ASTRONOMY 58.10(2015):104703.