The effect of wing deformation on unsteady aerodynamic mechanisms in hovering flapping flight
Numerical study using a three-dimensional immersed boundary method
T.A. Noyon (TU Delft - Aerospace Engineering)
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)
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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).