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Finite obstacle effect on the aerodynamic performance of a hovering wing
Yin B(银波)1; Yang GW(杨国伟)1; Prapamonthon P1,2
Corresponding AuthorYin, B.(yinbo@imech.ac.cn)
Source PublicationPHYSICS OF FLUIDS
2019-10-01
Volume31Issue:10Pages:12
ISSN1070-6631
AbstractThe 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.
DOI10.1063/1.5119046
Indexed BySCI ; EI
Language英语
WOS IDWOS:000506026700039
WOS KeywordIMMERSED-BOUNDARY METHOD ; EDGE VORTICES ; INSECT ; FORCES ; DEFORMATION ; ROTATION ; FLIGHT ; FLOWS
WOS Research AreaMechanics ; Physics
WOS SubjectMechanics ; Physics, Fluids & Plasmas
Funding ProjectNational Natural Science Foundation of China[11702297] ; National Key Research and Development Program of China[2017YFB0202802]
Funding OrganizationNational Natural Science Foundation of China ; National Key Research and Development Program of China
Classification一类/力学重要期刊
Ranking1
ContributorYin, B.
Citation statistics
Cited Times:3[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/81307
Collection流固耦合系统力学重点实验室
Affiliation1.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
Recommended Citation
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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