The effect of wing deformation on unsteady aerodynamic mechanisms in hovering flapping flight

Numerical study using a three-dimensional immersed boundary method

Master thesis (2014)

Authors

T.A. Noyon Aerospace Engineering

Contributors

H Bijl Aerospace Engineering (mentor)
B. W. van Oudheusden Aerodynamics (mentor)
W. Tay Aerodynamics (mentor)
C de Wagter Control & Simulation (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2014 Tijs Noyon
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Published Date

17-03-2014

Language

English

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Faculty

Aerospace Engineering

Abstract

This study investigated the effect of chord deformation on the unsteady aerodynamic mechanisms found in hovering flapping flight at a Reynolds number of Re = 2002. This was done in order to get a better understanding of the physics involved in flapping flight, which in turn could lead to improved Micro Aerial Vehicle (MAV) designs. A three-dimensional numerical study was performed using an immersed boundary method (IBM) with the discrete forcing approach. The solver was first validated against an experiment by Kim and Gharib (2011).

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