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)
Author(s)

T.A. Noyon (TU Delft - Aerospace Engineering)

Contributor(s)

H Bijl – Mentor (TU Delft - Aerospace Engineering)

B. W. van Oudheusden – Mentor (TU Delft - Aerodynamics)

WB Tay – Mentor (TU Delft - Aerodynamics)

Christophe de Wagter – Mentor (TU Delft - Control & Simulation)

Faculty
Aerospace Engineering
Copyright
© 2014 Tijs Noyon
More Info
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Publication Year
2014
Language
English
Copyright
© 2014 Tijs Noyon
Graduation Date
17-03-2014
Awarding Institution
Delft University of Technology
Programme
Aerospace Engineering | Aerodynamics and Wind Energy
Faculty
Aerospace Engineering
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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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