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The effect of the aerofoil thickness on the performance of the MAV scale cycloidal rotor

Published online by Cambridge University Press:  27 January 2016

Y. Hu ,
H.L. Zhang  and
C. Tan
H.L. Zhang
Affiliation:
School of aeronautics, Northwestern Polytechnic University, Xi’an, Shan Xi, China
C. Tan
Affiliation:
School of aeronautics, Northwestern Polytechnic University, Xi’an, Shan Xi, China
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Abstract

The numerical simulations for cycloidal propellers based on five aerofoils with different thickness are presented in this paper. The CFD simulation is based on sliding mesh and URANS. The results of CFD simulation indicates that all test cases share similar flow pattern. There are leading edge vortex and trailing-edge vortex due to blade dynamic stall. Interaction between the vortices shed from upstream blade and the downstream blade can be observed. There is variation of blade relative inflow velocity due to downwash in the cycloidal rotor cage. These factors result in large fluctuations of the aerodynamics forces on the blade. The comparison of the forces and flow pattern indicates that the thickness and leading edge radius of the aerofoil can significantly influent the flow pattern and hence the performance of the cycloidal propeller.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1213 , March 2015 , pp. 343 - 364
Copyright
Copyright © Royal Aeronautical Society 2015

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