Aerodynamic Performance of Wingtip-Mounted Propellers in Tractor and Pusher Configuration

Conference paper (2021)

Authors

T. Sinnige Flight Performance and Propulsion - Aerospace Engineering
R. Nederlof Flight Performance and Propulsion - Aerospace Engineering
N. van Arnhem Flight Performance and Propulsion - Aerospace Engineering
Research Group
Flight Performance and Propulsion (Aerospace Engineering) (TU Delft)
Copyright: © 2021 T. Sinnige, R. Nederlof, N. van Arnhem
DOI: https://doi.org/10.2514/6.2021-2511
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Published Date

2021

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Flight Performance and Propulsion

Abstract

Wingtip-mounted propellers are a promising solution for advanced propulsion integration on future (hybrid-)electric aircraft. Previous work has confirmed the favorable aerodynamic interactions between the propeller and the wing that occur for wingtip-mounted propellers in both tractor and pusher configuration. However, a direct comparison of the performance effects for the tractor and pusher configurations is unavailable in open literature. Moreover, the separate contributions of the propeller and wing forces to the overall system performance have not been sufficiently separated in previous studies. This paper presents the results of a wind-tunnel experiment performed at Delft University of Technology with a modular propeller-wing setup that addressed these knowledge gaps. A powered propeller model with a nacelle was installed at the tip of a cambered wing model. The nacelle could be reversed in order to change from tractor to pusher configuration. Measurements with an external balance quantified the system loading, while an internal balance provided a separate measurement of the propeller loading. The results highlight the differences between the interaction mechanisms for the tractor and pusher configurations. An assessment of the system performance showed that the pusher configuration required the lowest propeller shaft power to achieve a given system lift coefficient and net force coefficient in the flight direction. Power reductions of up to 9% were achieved compared to the tractor configuration for lift coefficients between 0.0 and 1.0 and net axial force coefficients between 0.00 (force balance in flight direction) and +0.08 (net positive force in flight direction).