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

文献类型：期刊论文

作者Chen, Jianqiang3,4; Yi, Shihe2; Li XL(李新亮)1; Han GL(韩桂来)1; Zhang, Yifeng3,4; Yang, Qiang4; Yuan, Xianxu3,4
刊名APPLIED THERMAL ENGINEERING
出版日期2021-07-25
卷号194页码:14
关键词Hypersonic boundary layer Stability Transition Thermal protection
ISSN号1359-4311
DOI10.1016/j.applthermaleng.2021.116931
通讯作者Yuan, Xianxu(yuanxianxu@cardc.cn)
英文摘要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.
分类号一类
WOS关键词LAMINAR-TURBULENT TRANSITION ; CROSS-FLOW ; TRANSIENT GROWTH ; NOSE BLUNTNESS ; SKIN-FRICTION ; GROUND TEST ; INSTABILITY ; STABILITY ; DISTURBANCES ; WAVES
资助项目National Key Research and Development Program of China[2016YFA0401200]
WOS研究方向Thermodynamics ; Energy & Fuels ; Engineering ; Mechanics
语种英语
WOS记录号WOS:000660532500003
资助机构National Key Research and Development Program of China
其他责任者Yuan, Xianxu
源URL[http://dspace.imech.ac.cn/handle/311007/86949]  
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.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
2.Natl Univ Def Technol, Coll Aerosp & Engn, Changsha 410073, Peoples R China;
3.China Aerodynam Res & Dev Ctr, Computat Aerodynam Inst, Mianyang 621000, Sichuan, Peoples R China;
4.China Aerodynam Res & Dev Ctr, State Key Lab Aerodynam, Mianyang 621000, Sichuan, 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.
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.

入库方式： OAI收割

来源：力学研究所

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