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Experimental investigation of aerofoil tonal noise at low Mach number

Published online by Cambridge University Press:  09 December 2021

Prateek Jaiswal Open the ORCID record for Prateek Jaiswal [Opens in a new window] ,
Yann Pasco ,
Gyuzel Yakhina  and
Stéphane Moreau Open the ORCID record for Stéphane Moreau [Opens in a new window]
Prateek Jaiswal
Affiliation:
Department of Mechanical Engineering, University of Sherbrooke, Sherbrooke, QC, J1K 2R1, Canada
Yann Pasco
Affiliation:
Department of Mechanical Engineering, University of Sherbrooke, Sherbrooke, QC, J1K 2R1, Canada
Gyuzel Yakhina
Affiliation:
Department of Mechanical Engineering, University of Sherbrooke, Sherbrooke, QC, J1K 2R1, Canada
Stéphane Moreau*
Affiliation:
Department of Mechanical Engineering, University of Sherbrooke, Sherbrooke, QC, J1K 2R1, Canada
*
†Email address for correspondence: [email protected]
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Abstract

This paper presents an experimental investigation of aerofoil tones emitted by a controlled-diffusion aerofoil at low Mach number ($0.05$), moderate Reynolds number based on the chord length ($1.4 \times 10^{5}$) and moderate incidence ($5^{\circ }$ angle of attack). Wall-pressure measurements have been performed along the suction side of the aerofoil to reveal the acoustic source mechanisms. In particular, a feedback loop is found to extend from the aerofoil trailing edge to the regions near the leading edge where the flow encounters a mean favourable pressure gradient, and consists of acoustic disturbances travelling upstream. Simultaneous wall-pressure, velocity and far-field acoustic measurements have been performed to identify the boundary-layer instability responsible for tonal noise generation. Causality correlation between far-field acoustic pressure and wall-normal velocity fluctuations has been performed, which reveals the presence of a Kelvin–Helmholtz-type modal shape within the velocity disturbance field. Tomographic particle image velocimetry measurements have been performed to understand the three-dimensional aspects of this flow instability. These measurements confirm the presence of large two-dimensional rollers that undergo three-dimensional breakdown just upstream of the trailing edge. Finally, modal decomposition of the flow has been carried out using proper orthogonal decomposition, which demonstrates that the normal modes are responsible for aerofoil tonal noise. The higher normal modes are found to undergo regular modulations in the spanwise direction. Based on the observed modal shape, an explanation of aerofoil tonal noise amplitude reduction is given, which has been previously reported in modular or serrated trailing-edge aerofoils.

JFM classification

Acoustics: Aeroacoustics Boundary Layers: Boundary layer stability Turbulent Flows: Turbulent transition
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 932 , 10 February 2022 , A37
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Copyright
© The Author(s), 2021. Published by Cambridge University Press

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References

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