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Experimental Investigation of Leading Edge Flow Control for a Rigid Flapping Wing Using Plasma Actuator

Taheri, Benyamin | 2018

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 52494 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Ebrahimi, Abbas
  7. Abstract:
  8. Using flapping motions, birds produce aerodynamic forces required to fly. Flapping wing aerodynamics is one of the most complicated problems in unsteady aerodynamic field. Experimental study on the structure, the way of production and growth and the feasibility of controlling the leading edge vortex are the main goals of this research in order to improve the aerodynamic performance of flapping wings. Since leading edge vortex structure appears in both upstroke and downstroke of a complete storke in flapping motion, controlling the structure in one of the half-storkes can provide the possibility of having a better aerodynamic performance. In this research, the wing is designed and manufactured with under 30 centimeter span and the mechanism of flapping wing is designed and manufactured with under 3 hertz frequency in flapping motion. The experimental visualization tests of leading edge vortex structure are taken in various frequencies of flapping and various percentage of wing span all in static condition without any front wind velocity and the location of leading edge vortex were measured. Already the feasibility of changing the power of leading edge vortex were investigated using various layouts of plasma actuator installed on wing during the experiments
  9. Keywords:
  10. Plasma Actuator ; Flow Control ; Leading Edge Vortex ; Detection ; Unsteady Aerodynamic

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