Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone

doi:10.1016/j.applthermaleng.2021.116931

	Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone
	Chen, Jianqiang 1,2; Yi, Shihe 3; Li XL(李新亮)4 ; Han GL(韩桂来)4 ; Zhang, Yifeng 1,2; Yang, Qiang 1; Yuan, Xianxu 1,2
通讯作者	Yuan, Xianxu([email protected])
发表期刊	APPLIED THERMAL ENGINEERING
	2021-07-25
卷号	194 页码:14
ISSN	1359-4311
摘要	This article reviews the hypersonic laminar-turbulent boundary layer transition over a blunt circular cone under support of the National Key Research and Development Program of China (contract No. 2016YFA0401200). Various approaches, including theoretical, numerical, experimental and flight test, are combined to obtain a complete perspective of the transition process as well as some fundamental issues for this kind of flow. The interaction between freestream disturbances and the front shock wave is analysed theoretically, and multiple receptivity routes are unveiled using a sub-zone analysis technique. The entire transition process is captured using high-resolution nano-tracer-based planar laser scattering technique in a quiet windtunnel as well as large-scale high-fidelity direct numerical simulations. Using dynamic mode decomposition, the relationship between the second Mach mode and the low-frequency mode in the late stage of the transition is revealed. The "transition reversal" phenomenon is recovered in two of our conventional windtunnels. The numerical results show that leading-edge receptivity varies significantly for different cone bluntness, which might be responsible for the "transition reversal" phenomenon. For the cone at angles of attack, new instabilities including the leeward centerline vortex instability and the crossflow instability, occur and can significantly promote the transition process. A newly developed C. Re. transition model can give a good transition front prediction compared to the experimental data. The flight test for a cone model conducted within this project is reviewed, and the correlation between the ground experimental data and the flight data is established.
关键词	Hypersonic boundary layer Stability Transition Thermal protection
DOI	10.1016/j.applthermaleng.2021.116931
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000660532500003
关键词[WOS]	LAMINAR-TURBULENT TRANSITION ; CROSS-FLOW ; TRANSIENT GROWTH ; NOSE BLUNTNESS ; SKIN-FRICTION ; GROUND TEST ; INSTABILITY ; STABILITY ; DISTURBANCES ; WAVES
WOS研究方向	Thermodynamics ; Energy & Fuels ; Engineering ; Mechanics
WOS类目	Thermodynamics ; Energy & Fuels ; Engineering, Mechanical ; Mechanics
资助项目	National Key Research and Development Program of China[2016YFA0401200]
项目资助者	National Key Research and Development Program of China
论文分区	一类
力学所作者排名	3
RpAuthor	Yuan, Xianxu
引用统计	被引频次：17[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/311007/86950
专题	高温气体动力学国家重点实验室
作者单位	1.China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Sichuan, Peoples R China; 2.China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang 621000, Sichuan, Peoples R China; 3.Natl Univ Def Technol, Coll Aerosp & Engn, Changsha 410073, Peoples R China; 4.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Chen, Jianqiang,Yi, Shihe,Li XL,et al. Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone[J]. APPLIED THERMAL ENGINEERING,2021,194:14.Rp_Au:Yuan, Xianxu
APA	Chen, Jianqiang.,Yi, Shihe.,李新亮.,韩桂来.,Zhang, Yifeng.,...&Yuan, Xianxu.(2021).Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone.APPLIED THERMAL ENGINEERING,194,14.
MLA	Chen, Jianqiang,et al."Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone".APPLIED THERMAL ENGINEERING 194(2021):14.

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