Reduced dimension modeling of leading edge turbulent interaction noise
Reduced dimension modeling of leading edge turbulent interaction noise
A computational aeroacoustics approach is used to model the effects of real airfoil geometry on leading edge turbulent interaction noise for symmetric airfoils at zero angle of attack. For the first time, one-component (transverse), two-component (transverse and streamwise), and three-component (transverse, streamwise, and spanwise) synthesized turbulent disturbances are modeled instead of single frequency transverse gusts, which previous computational studies of leading edge noise have been confined to. The effects of the inclusion of streamwise and spanwise disturbances on the noise are assessed, and it is shown that accurate noise predictions for symmetric airfoils can be made by modeling only the transverse disturbances, which reduces the computational expense of simulations. Additionally, the two-component turbulent synthesis method is used to model the effects of airfoil thickness on the noise for thicknesses ranging from 2% to 12%. By using sufficient airfoil thicknesses to show trends, it is found that airfoil thickness will reduce the noise at high frequency, and that the sound power P will reduce linearly with increasing airfoil thickness.
computational aeroacoustics, leading edge noise, linearized euler equations, turbulencesynthesis
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
Node-Langlois, Thomas
746d8e36-a76a-449d-95d2-0da56af9ec44
14 June 2014
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
Node-Langlois, Thomas
746d8e36-a76a-449d-95d2-0da56af9ec44
Gill, James, Zhang, Xin, Joseph, Phillip F. and Node-Langlois, Thomas
(2014)
Reduced dimension modeling of leading edge turbulent interaction noise.
20th AIAA/CEAS Aeroacoustics Conference, Atlanta, United States.
16 - 20 Jun 2014.
20 pp
.
(doi:10.2514/6.2014-2321).
Record type:
Conference or Workshop Item
(Paper)
Abstract
A computational aeroacoustics approach is used to model the effects of real airfoil geometry on leading edge turbulent interaction noise for symmetric airfoils at zero angle of attack. For the first time, one-component (transverse), two-component (transverse and streamwise), and three-component (transverse, streamwise, and spanwise) synthesized turbulent disturbances are modeled instead of single frequency transverse gusts, which previous computational studies of leading edge noise have been confined to. The effects of the inclusion of streamwise and spanwise disturbances on the noise are assessed, and it is shown that accurate noise predictions for symmetric airfoils can be made by modeling only the transverse disturbances, which reduces the computational expense of simulations. Additionally, the two-component turbulent synthesis method is used to model the effects of airfoil thickness on the noise for thicknesses ranging from 2% to 12%. By using sufficient airfoil thicknesses to show trends, it is found that airfoil thickness will reduce the noise at high frequency, and that the sound power P will reduce linearly with increasing airfoil thickness.
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Gill2014.pdf
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More information
e-pub ahead of print date: 13 June 2014
Published date: 14 June 2014
Venue - Dates:
20th AIAA/CEAS Aeroacoustics Conference, Atlanta, United States, 2014-06-16 - 2014-06-20
Keywords:
computational aeroacoustics, leading edge noise, linearized euler equations, turbulencesynthesis
Organisations:
Aeronautics, Astronautics & Comp. Eng
Identifiers
Local EPrints ID: 366550
URI: http://eprints.soton.ac.uk/id/eprint/366550
PURE UUID: 9594c323-f197-4157-b4ad-f48f065dda37
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Date deposited: 02 Jul 2014 15:00
Last modified: 14 Mar 2024 17:11
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Author:
Xin Zhang
Author:
Thomas Node-Langlois
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