Flow Structures Around a Flapping-Wing Micro Air Vehicle Performing a Clap-and-Peel Motion

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2017-04-01

Author

Perçin, Mustafa
Remes, Bart

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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The vortical flow structures generated by the flapping wings of the DelFly II micro air vehicle in hovering flight configuration are investigated using particle image velocimetry. Synchronous force measurements are carried out to establish the relation between the unsteady forces and force generation mechanisms: particularly, the leading-edge vortex and the clap-and-peel motion. The formation of conical leading-edge vortices on both wings is revealed, which occurs rapidly at the start of the outstroke as a result of the wing-wing interaction. The leading-edge vortices of the outstroke interact with those of the instroke, which are shed and, by mutual induction, advect upstream as a vortex pair at the end of previous instroke. The leading-edge vortex pairs induce a strong inflow into the region formed between the upper and lower wings during the peeling phase, resulting in the formation of a low-pressure region. This, together with the leading-edge vortices and a momentum increase formed by the clap, accounts for the generation of relatively higher forces during the outstroke. The cycle-averaged forces are estimated with reasonable accuracy by means of a momentum-based approach using wake velocity information with an average error of 15%.

Subject Keywords

Leading-edge vortex, Unsteady aerodynamic model, Hover performance, Wake structure, Visualization, Design, Vortices

URI

https://hdl.handle.net/11511/48140

Journal

AIAA JOURNAL

DOI

https://doi.org/10.2514/1.j055146

Collections

Department of Aerospace Engineering, Article

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Flow Visualization in the Wake of the Flapping-Wing MAV ’DelFly II’ in Forward Flight Perçin, Mustafa; van Oudheusden, Bas W.; Remes, Bart; Ruijsink, R; de Wagter, C (2012-06-25) Time-resolved velocity field measurements in the wake of the flapping wings of the DelFly II Micro Aerial Vehicle (MAV) in forward flight configuration were obtained by Stereoscopic Particle Image Velocimetry (Stereo-PIV). The PIV measurements were performed at several spanwise planes in the wake of the flapping wings and at a high framing rate to allow a reconstruction of the temporal development of the three dimensional wake structures throughout the flapping cycle. The wake reconstruction was performed b...
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Aerodynamic characterization of 'DelFly Micro' in forward flight configuration by force measurements and flow field visualization Deng, Shuanghou; Perçin, Mustafa; van Oudheusden, Bas (2015-01-01) This study explores the flow structures and unsteady force generation mechanisms of a flapping-wing micro air vehicle 'DelFly Micro' in forward flight configuration. Stereoscopic Particle Image Velocimetry (Stereo-PIV) measurements were performed to acquire three dimensional flow fields in the wake. Six components of forces and moments were captured simultaneously by use of a miniature force sensor.

Citation Formats

M. Perçin and B. Remes, “Flow Structures Around a Flapping-Wing Micro Air Vehicle Performing a Clap-and-Peel Motion,” AIAA JOURNAL, pp. 1251–1264, 2017, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/48140.