Aerodynamics of wing with oscillating wingtip Flapper

Sergey V Shkarayev, Erlong Su, Longfei Zhao

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Scopus citations

Abstract

In the present study, a membrane oscillating flapper was connected to the wingtip of a conventional rigid wing. Stroke-average aerodynamic forces were measured for the range of flapping frequency, showing significant increase in the lift coefficient and lift-to-drag ratio for the wing with flapper. Wake structures were visualized and analyzed using smoke-wire techniques and 2D phase-locked PIV. Major vortex patterns were deduced from the observations: two undulating vortex tubes and a vortex ring. Experimental data indicate that two undulating vortices are periodically closed by a cross-stream vortex. The vortex ring sheds from the flapper during the second half of the upstroke and on pronation and dissipates at a short distance behind the wing. The circulation of undulating vortices and of the ring decreases significantly with increasing distance from the wing downstream, while the decrease of the vortex core size is minimal.

Original languageEnglish (US)
Title of host publication34th AIAA Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104374
DOIs
StatePublished - Jan 1 2016
Event34th AIAA Applied Aerodynamics Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Publication series

Name34th AIAA Applied Aerodynamics Conference

Other

Other34th AIAA Applied Aerodynamics Conference, 2016
CountryUnited States
CityWashington
Period6/13/166/17/16

Keywords

  • Drag
  • Flapping
  • Lift
  • Vortex
  • Wake
  • Wing

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering

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  • Cite this

    Shkarayev, S. V., Su, E., & Zhao, L. (2016). Aerodynamics of wing with oscillating wingtip Flapper. In 34th AIAA Applied Aerodynamics Conference (34th AIAA Applied Aerodynamics Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2016-3119