Mitigation of Pusher-Propeller Installation Effects by Pylon Trailing-Edge Blowing

This paper presents an experimental assessment of the working principles of pylon trailing-edge blowing for the mitigation of the interaction between a pusher propeller and its associated pylon. The experiments were performed at the Large Low-Speed Facility of the German–Dutch wind tunnels, using a...

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Bibliographic Details
Published in:Journal of aircraft 2017-01, Vol.54 (1), p.292-300
Main Authors: Sinnige, Tomas, Ragni, Daniele, Eitelberg, Georg, Veldhuis, Leo L. M
Format: Article
Language:English
Subjects:
Aerodynamics
Aerospace engineering
Aircraft
Assessments
Blades
Blowing
Fines & penalties
Load fluctuation
Low speed
Measurement techniques
Microphones
Noise
Propellers
Pylons
Trailing edges
Velocimetry
Velocity
Wind tunnels
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Summary:This paper presents an experimental assessment of the working principles of pylon trailing-edge blowing for the mitigation of the interaction between a pusher propeller and its associated pylon. The experiments were performed at the Large Low-Speed Facility of the German–Dutch wind tunnels, using a powered propeller model and an upstream pylon equipped with a trailing-edge blowing system. Inflow microphone measurements demonstrated the impact of pylon installation on the propeller’s tonal noise emissions, with increases of up to 16 dB relative to the isolated propeller. Analysis of the unsteady blade pressures showed that this installation effect was caused by the impulsive increase in blade loading during the pylon-wake passage. The efficacy of pylon trailing-edge blowing to reduce the momentum deficit in the pylon wake was confirmed by stereoscopic particle-image-velocimetry measurements between the pylon and the propeller. Consequently, application of the pylon-blowing system alleviated the pylon-installation effects at the source. At an intermediate thrust setting, the rms of the blade-load fluctuations due to the wake encounter was reduced by up to 60%, resulting in noise emissions approximately equal to those recorded for the isolated propeller.
ISSN:0021-8669
1533-3868
DOI:10.2514/1.C034000