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Blade element momentum theory extended to model low Reynolds number propeller performance

Part of: APISAT 2015

Published online by Cambridge University Press:  03 May 2017

R. MacNeill  and
D. Verstraete
R. MacNeill*
Affiliation:
The University of Sydney, School of Aerospace Mechanical and Mechatronic Engineering, Sydney, Australia
D. Verstraete
Affiliation:
The University of Sydney, School of Aerospace Mechanical and Mechatronic Engineering, Sydney, Australia
*
[email protected]
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Abstract

Propellers are the predominant propulsion source for small unmanned aerial vehicles. At low advance ratios, large sections of the propeller blade can be stalled, and the Reynolds number faced by each blade can be low. This leads to difficulties in modelling propeller performance, as the aerodynamic models coupled with blade element methods usually only provide aerodynamic data for an assumed aerofoil section, for a small angle-of-attack range and for a single Reynolds number, while rotational effects are often ignored. This is specifically important at low advance ratios, and a consistent evaluation of the applicability of various methods to improve aerodynamic modelling is not available. To provide a systematic appraisal, three-dimensional (3D) scanning is used to obtain the aerofoil sections that make up a propeller blade. An aerodynamic database is formed using each extracted aerofoil section, across a wide range of angles of attack and Reynolds numbers. These databases are then modified to include the effects of rotation. When compared with experimental results, significant improvement in modelling accuracy is shown at low advance ratios relative to a generic blade element-momentum model, particularly for smaller propellers. Notably, when considering small propeller performance, efficiency modelling is improved from within 30% relative to experimental data to within 5% with the use of the extended blade element momentum theory method. The results show that combining Viterna and Corrigan flat plate theory with the Corrigan and Schillings stall delay model consistently yields the closest match with experimental data.

Keywords

Propellerunmanned aircraftblade elementlow Reynolds number
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1240 , June 2017 , pp. 835 - 857
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This is an adaptation of a paper first presented at the 2015 Asia-Pacific International Symposium on Aerospace Technology in Cairns, Australia

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