Finite obstacle effect on the aerodynamic performance of a hovering wing

doi:10.1063/1.5119046

IMECH-IR > 流固耦合系统力学重点实验室

	Finite obstacle effect on the aerodynamic performance of a hovering wing
	Yin B(银波)1 ; Yang GW(杨国伟)1 ; Prapamonthon P 1,2
通讯作者	Yin, B.(yinbo@imech.ac.cn)
发表期刊	PHYSICS OF FLUIDS
	2019-10-01
卷号	31 期号:10 页码:12
ISSN	1070-6631
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.
DOI	10.1063/1.5119046
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000506026700039
关键词[WOS]	IMMERSED-BOUNDARY METHOD ; EDGE VORTICES ; INSECT ; FORCES ; DEFORMATION ; ROTATION ; FLIGHT ; FLOWS
WOS研究方向	Mechanics ; Physics
WOS类目	Mechanics ; Physics, Fluids & Plasmas
资助项目	National Natural Science Foundation of China[11702297] ; National Key Research and Development Program of China[2017YFB0202802]
项目资助者	National Natural Science Foundation of China ; National Key Research and Development Program of China
论文分区	一类/力学重要期刊
力学所作者排名	1
RpAuthor	Yin, B.
引用统计	被引频次：10[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/311007/81307
专题	流固耦合系统力学重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, Key Lab Mech Fluid Solid Coupling Syst, Beijing, Peoples R China; 2.King Mongkuts Inst Technol Ladkrabang, Int Acad Aviat Ind, Dept Aeronaut Engn, Bangkok, Thailand
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.

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