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Effects of real airfoil geometry on leading edge gust interaction noise

Effects of real airfoil geometry on leading edge gust interaction noise
Effects of real airfoil geometry on leading edge gust interaction noise
High-order computational aeroacoustic methods are applied to the modeling of noise due to interactions between gusts and the leading edge of real symmetric airfoils. The effects of airfoil thickness and leading edge radius on noise are investigated systematically and in-dependently for the first time, at higher frequencies than previously used in computational methods. Single frequency harmonic gusts are interacted with airfoils of varying geometry at zero angle of attack. Increases in both leading edge radius and thickness are found to reduce the predicted noise. This noise reduction effect becomes greater with increasing frequency and Mach number. The dominant noise reduction mechanism for airfoils with real geometry is found to be related to the leading edge stagnation region. The assumption of uniform meanflow is shown to be invalid when modeling the leading edge noise of real airfoils. However, accurate results are still obtained when an inviscid meanflow is assumed. The accuracy of analytic flat plate solutions can be expected to decrease with increasing airfoil thickness, leading edge radius, gust frequency and Mach number.
Gill, James
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Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip
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Node-Langlois, Thomas
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Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip
9c30491e-8464-4c9a-8723-2abc62bdf75d
Node-Langlois, Thomas
746d8e36-a76a-449d-95d2-0da56af9ec44

Gill, James, Zhang, Xin, Joseph, Phillip and Node-Langlois, Thomas (2013) Effects of real airfoil geometry on leading edge gust interaction noise. 19th AIAA/CEAS Aeroacoustics Conference, Berlin, Germany. 27 - 29 May 2013. (doi:10.2514/6.2013-2203).

Record type: Conference or Workshop Item (Paper)

Abstract

High-order computational aeroacoustic methods are applied to the modeling of noise due to interactions between gusts and the leading edge of real symmetric airfoils. The effects of airfoil thickness and leading edge radius on noise are investigated systematically and in-dependently for the first time, at higher frequencies than previously used in computational methods. Single frequency harmonic gusts are interacted with airfoils of varying geometry at zero angle of attack. Increases in both leading edge radius and thickness are found to reduce the predicted noise. This noise reduction effect becomes greater with increasing frequency and Mach number. The dominant noise reduction mechanism for airfoils with real geometry is found to be related to the leading edge stagnation region. The assumption of uniform meanflow is shown to be invalid when modeling the leading edge noise of real airfoils. However, accurate results are still obtained when an inviscid meanflow is assumed. The accuracy of analytic flat plate solutions can be expected to decrease with increasing airfoil thickness, leading edge radius, gust frequency and Mach number.

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Published date: 28 May 2013
Venue - Dates: 19th AIAA/CEAS Aeroacoustics Conference, Berlin, Germany, 2013-05-27 - 2013-05-29
Organisations: Aeronautics, Astronautics & Comp. Eng

Identifiers

Local EPrints ID: 357448
URI: http://eprints.soton.ac.uk/id/eprint/357448
PURE UUID: a0bc5eb1-a993-44df-88c4-4baef714cd10

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Date deposited: 08 Oct 2013 12:16
Last modified: 16 Dec 2019 20:29

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Contributors

Author: James Gill
Author: Xin Zhang
Author: Phillip Joseph
Author: Thomas Node-Langlois

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