Experimental and numerical study on wingtip mounted propellers for low aspect ratio UAV design

Master thesis (2012)

Authors

Contributors

G. Eitelberg (mentor)
L.L.M. Veldhuis (mentor)
Faculty
Aerospace Engineering (Aerospace Engineering) (TU Delft)
Copyright: © Delft University of Technology
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Published Date

30-03-2012

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Faculty

Aerospace Engineering

Abstract

The effects of the propulsion element in a propeller-driven aircraft are of paramount importance to the overall performance, stability and control characteristics of the system. Positioning the propeller at the wing's tip has been shown to improve the aerodynamic behavior of the aircraft. The complexity of the ow field associated with such a design, however, demands a clear understanding of the propeller-wing interaction. The goal of this masters thesis project is to study the aerodynamic effects present in a wingtip mounted propeller configuration for a low aspect ratio wing. In doing so, a wind tunnel experiment has been conducted for a simple, half-wing configuration. In addition, a numerical study has been performed with a tool, specially developed for treating wingtip mounted propellers.