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Finite obstacle effect on the aerodynamic performance of a hovering wing

文献类型：期刊论文

作者Yin B(银波)2; Yang GW(杨国伟)2; Prapamonthon P1,2
刊名PHYSICS OF FLUIDS
出版日期2019-10-01
卷号31期号:10页码:12
ISSN号1070-6631
DOI10.1063/1.5119046
通讯作者Yin, B.(yinbo@imech.ac.cn)
英文摘要The finite obstacle effect on the aerodynamic performance of a normal hovering wing is studied using the immersed boundary method. Phenomena of a two-dimensional wing hovering above, under, or on the side of a circular obstacle are presented. Parameters including obstacle size, distance, location, and flapping angle are investigated to study how the aerodynamic force and flow field are affected. The diameter of the obstacle ranges from 0.5c to 12c and the distance between the centroid of the wing and obstacle surface from 0.5c to 6c (c is the wing chord length). Previous observations of ground effects including force enhancement, reduction, and recovery occur similarly when the wing hovers above the obstacle of diameter greater than 2c. However, finite obstacles affect the aerodynamic performance differently when the size shrinks to a critical value. Force drops when the wing moves close and rises when moving away, opposite to the ground effect. As flapping angle amplitude increases, the force change tends to be consistent for different-sized obstacles. The top or side effect shows a different influence on the force change. Force monotonically increases as the distance decreases when the wing hovers under the obstacle. The side effect places a less important factor on the aerodynamic performance. All force changes under such circumstance are less than 13% referring to nonobstacle result. The gap between the leading or trailing edge of the wing and obstacle surface plays a significant role in the leading and trailing edge vortices generating, shedding, and pairing, which greatly affects the force change. Published under license by AIP Publishing.
分类号一类/力学重要期刊
WOS关键词IMMERSED-BOUNDARY METHOD ; EDGE VORTICES ; INSECT ; FORCES ; DEFORMATION ; ROTATION ; FLIGHT ; FLOWS
资助项目National Natural Science Foundation of China[11702297] ; National Key Research and Development Program of China[2017YFB0202802]
WOS研究方向Mechanics ; Physics
语种英语
WOS记录号WOS:000506026700039
资助机构National Natural Science Foundation of China ; National Key Research and Development Program of China
其他责任者Yin, B.
源URL[http://dspace.imech.ac.cn/handle/311007/81306]  
专题力学研究所_流固耦合系统力学重点实验室(2012-)
作者单位1.King Mongkuts Inst Technol Ladkrabang, Int Acad Aviat Ind, Dept Aeronaut Engn, Bangkok, Thailand
2.Chinese Acad Sci, Inst Mech, Key Lab Mech Fluid Solid Coupling Syst, Beijing, Peoples R China;
推荐引用方式
GB/T 7714		 Yin B,Yang GW,Prapamonthon P. Finite obstacle effect on the aerodynamic performance of a hovering wing[J]. PHYSICS OF FLUIDS,2019,31(10):12.
APA 银波,杨国伟,&Prapamonthon P.(2019).Finite obstacle effect on the aerodynamic performance of a hovering wing.PHYSICS OF FLUIDS,31(10),12.
MLA 银波,et al."Finite obstacle effect on the aerodynamic performance of a hovering wing".PHYSICS OF FLUIDS 31.10(2019):12.

入库方式： OAI收割

来源：力学研究所

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