Analytical and experimental investigation into the effects of leading-edge radius on gust–aerofoil interaction noise
Analytical and experimental investigation into the effects of leading-edge radius on gust–aerofoil interaction noise
This paper investigates the effects of local leading-edge geometry on unsteady aerofoil interaction noise. Analytical results are obtained by extending previous work for parabolic leading edges to leading edges of the form xm for 0 < m < 1. Rapid distortion theory governs the interaction of an unsteady vortical perturbation with a rigid aerofoil in compressible steady mean flow that is uniform far upstream. For high-frequency gusts interacting with aerofoils of small total thickness this allows a matched asymptotic solution to be obtained. This paper mainly focusses on obtaining the analytic solution in the leading-edge inner region, which is the dominant term in determining the total far-field acoustic directivity, and contains the effects of the local leading-edge geometry. Experimental measurements for the noise generated by aerofoils with different leading-edge nose radii in uniform flow with approximate homogeneous, isotropic turbulence are also presented. Both experimental and analytic results predict that a larger nose radius generates less overall noise in low-Mach-number flow. By considering individual terms in the analytic solution, this paper is able to propose reasons behind this result.
acoustics, aeroacoustics
780-808
Ayton, Lorna J.
5e1d9202-7a93-4d53-8db9-8a8efe37d4d6
Paruchuri, Chaitanya
5c1def64-6347-4be3-ac2d-b9f6a314b81d
25 October 2017
Ayton, Lorna J.
5e1d9202-7a93-4d53-8db9-8a8efe37d4d6
Paruchuri, Chaitanya
5c1def64-6347-4be3-ac2d-b9f6a314b81d
Ayton, Lorna J. and Paruchuri, Chaitanya
(2017)
Analytical and experimental investigation into the effects of leading-edge radius on gust–aerofoil interaction noise.
Journal of Fluid Mechanics, 829, .
(doi:10.1017/jfm.2017.594).
Abstract
This paper investigates the effects of local leading-edge geometry on unsteady aerofoil interaction noise. Analytical results are obtained by extending previous work for parabolic leading edges to leading edges of the form xm for 0 < m < 1. Rapid distortion theory governs the interaction of an unsteady vortical perturbation with a rigid aerofoil in compressible steady mean flow that is uniform far upstream. For high-frequency gusts interacting with aerofoils of small total thickness this allows a matched asymptotic solution to be obtained. This paper mainly focusses on obtaining the analytic solution in the leading-edge inner region, which is the dominant term in determining the total far-field acoustic directivity, and contains the effects of the local leading-edge geometry. Experimental measurements for the noise generated by aerofoils with different leading-edge nose radii in uniform flow with approximate homogeneous, isotropic turbulence are also presented. Both experimental and analytic results predict that a larger nose radius generates less overall noise in low-Mach-number flow. By considering individual terms in the analytic solution, this paper is able to propose reasons behind this result.
Text
Draft2
- Accepted Manuscript
Text
Final
- Version of Record
Restricted to Repository staff only
Request a copy
More information
Accepted/In Press date: 17 August 2017
e-pub ahead of print date: 26 September 2017
Published date: 25 October 2017
Keywords:
acoustics, aeroacoustics
Identifiers
Local EPrints ID: 419010
URI: http://eprints.soton.ac.uk/id/eprint/419010
ISSN: 0022-1120
PURE UUID: cfd5be02-427f-4694-9bea-0d2dcaf38ee8
Catalogue record
Date deposited: 27 Mar 2018 16:31
Last modified: 16 Mar 2024 05:51
Export record
Altmetrics
Contributors
Author:
Lorna J. Ayton
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics