Alleviation of Propeller-slipstream-induced unsteady pylon loading by a flow-permeable leading edge

Journal article (2019)

Authors

T. Sinnige Flight Performance and Propulsion - Aerospace Engineering
B. della Corte Flight Performance and Propulsion - Aerospace Engineering
R. de Vries Flight Performance and Propulsion - Aerospace Engineering
F. Avallone Wind Energy - Aerospace Engineering
R. Merino Martinez Aircraft Noise and Climate Effects - Aerospace Engineering
D. Ragni Wind Energy - Aerospace Engineering
G. Eitelberg Flight Performance and Propulsion - Aerospace Engineering
L.L.M. Veldhuis Flight Performance and Propulsion - Aerospace Engineering
Research Group
Flight Performance and Propulsion (Aerospace Engineering) (TU Delft)
Copyright: © 2019 T. Sinnige, B. della Corte, R. de Vries, F. Avallone, R. Merino Martinez, D. Ragni, G. Eitelberg, L.L.M. Veldhuis
DOI: https://doi.org/10.2514/1.C035250
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Published Date

2019

Language

English

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Flight Performance and Propulsion

Abstract

The impingement of a propeller slipstream on a downstream surface causes unsteady loading, which may lead to vibrations responsible for structure-borne noise. A low-speed wind-tunnel experiment was performed to quantify the potential of a flow-permeable leading edge to alleviate the slipstream-induced unsteady loading. For this purpose, a tractor propeller was installed at the tip of a pylon featuring a replaceable leading-edge insert in the region of slipstream impingement. Tests were carried out with four flow-permeable inserts, with different hole diameters and cavity depths, and a baseline solid insert. Particle-image-velocimetry measurements showed that the flow through the permeable surface caused an increase in boundary-layer thickness on the pylon's suction side. This led to a local drag increase and reduced lift, especially for angles of attack above 6 deg. Furthermore, it amplified the viscous interaction with the propeller tip-vortex cores, reducing the velocity fluctuations near the pylon surface by up to 35%. Consequently, lower tonal noise emissions from the pylon were measured in the far field. This suggests that the desired reduction in surface pressure fluctuations was achieved by application of the flow-permeable leading edge.

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