| 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 Author | Yin, B.([email protected]) |
| Source Publication | PHYSICS OF FLUIDS
 |
| 2019-10-01 | |
| Volume | 31Issue:10Pages:12 |
| ISSN | 1070-6631 |
| Abstract | 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 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000506026700039 |
| WOS Keyword | IMMERSED-BOUNDARY METHOD ; EDGE VORTICES ; INSECT ; FORCES ; DEFORMATION ; ROTATION ; FLIGHT ; FLOWS |
| WOS Research Area | Mechanics ; Physics |
| WOS Subject | Mechanics ; Physics, Fluids & Plasmas |
| Funding Project | National Natural Science Foundation of China[11702297] ; National Key Research and Development Program of China[2017YFB0202802] |
| Funding Organization | National Natural Science Foundation of China ; National Key Research and Development Program of China |
| Classification | 一类/力学重要期刊 |
| Ranking | 1 |
| Contributor | Yin, B. |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/81307 |
| Collection | 流固耦合系统力学重点实验室 |
| Affiliation | 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 |
| 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.Rp_Au:Yin, B. |
| 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. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| Jp2019513.pdf（5326KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment