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Blade Element Momentum Method for Propeller Under Nonaxial Flow

Blade Element Momentum Method for Propeller Under Nonaxial Flow This paper presents a three-dimensional blade element momentum method to estimate aerodynamic forces and moments of a propeller under nonaxial flow. In the momentum theory part, the axial and normal elements in the velocity change are included for the estimation of the thrust and the normal force, and the rotating elements are introduced for the estimation of the counter-torque and the p-factor moment. In the blade element part, multiple coordinate systems are introduced to compute the local velocity and the angle-of-attack at the blade element. Then the forces and moments are averaged during the one revolution of the element, to be compared to those computed in the momentum theory. An iterative numerical method is applied to match the two parts to compute the resulting forces and moments. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

Blade Element Momentum Method for Propeller Under Nonaxial Flow

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References (19)

Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2022. Springer Nature or its licensor holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-022-00535-7
Publisher site
See Article on Publisher Site

Abstract

This paper presents a three-dimensional blade element momentum method to estimate aerodynamic forces and moments of a propeller under nonaxial flow. In the momentum theory part, the axial and normal elements in the velocity change are included for the estimation of the thrust and the normal force, and the rotating elements are introduced for the estimation of the counter-torque and the p-factor moment. In the blade element part, multiple coordinate systems are introduced to compute the local velocity and the angle-of-attack at the blade element. Then the forces and moments are averaged during the one revolution of the element, to be compared to those computed in the momentum theory. An iterative numerical method is applied to match the two parts to compute the resulting forces and moments.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: Apr 1, 2023

Keywords: Propeller; Blade element momentum method; Nonaixal flow

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