Lift from spanwise flow in simple flapping wings

被引：0

作者：

Hong, Youngsun ^{[1
,2
,3
,4
]}

Altman, Aaron ^{[1
,2
,4
]}

机构：

[1] University of Dayton, Dayton, OH 45469-0238, United States

[2] Department of Mechanical and Aerospace Engineering, 300 College Park

[3] Korean Air Force

[4] AIAA

来源：

Journal of Aircraft | 1600年 / 45卷 / 04期

关键词：

Spanwise flow contributes to lift in thin flat-plate zero-pitch-angle flapping wings in quiescent air. It is reasonable to maintain only the kinematics and mechanical complexity absolutely necessary in developing flapping-wing micro air vehicles. This study continues the quantification of the lift generated from a flapping motion of absolute minimum complexity thought to be capable of generating lift. A flapping-wing micro air vehicle with rectangular planform wings fabricated in-house (semispan aspect ratios from 1.5 to 4.0) was used to quantify the contributions to lift from flow along the span of wings at numerous points throughout the flapping cycle under a variety of operating conditions (3-6 Hz and Reynolds numbers of 6000-15,000). These experiments were performed for several aspect ratios for flatplate and spanwise-carnbered wings. The lift force was quantified experimentally using a force transducer and a high-speed camera. Digital particle image velocimetry was used to determine the lift contributions of spanwise flow to the total measured lift. Additionally, the presence of spanwise camber was shown to affect the transient lift behavior. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved;

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摘要：

Conference article (CA)

引用

页码：1206 / 1216