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 (supervisor 1)
B.W. van Oudheusden Aerodynamics - Aerospace Engineering (supervisor 1)
W. Tay Aerodynamics - Aerospace Engineering (supervisor 1)
C. de Wagter (supervisor 1)
Faculty
Aerospace Engineering
Copyright: © 2014 Tijs Noyon
More Info
expand_more

Published Date

17-03-2014

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

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).

Files

Noyon_T..pdf
(.pdf | 19.9 Mb)