Single velocity-component modeling of leading edge turbulence
interaction noise
Single velocity-component modeling of leading edge turbulence
interaction noise
A computational aeroacoustics approach is used to predict leading edge turbulence interaction noise for real airfoils. One-component (transverse), two-component (transverse and streamwise), and three-component (transverse, streamwise, and spanwise) synthesized turbulence disturbances are modeled instead of harmonic transverse gusts, to which previous computational studies of leading edge noise have often been confined. The effects of the inclusion of streamwise and spanwise disturbances on the noise are assessed. It is shown that accurate noise predictions can be made by modeling only transverse disturbances which reduces the computational expense of simulations. The accuracy of using only transverse disturbances is assessed for symmetric and cambered airfoils, and also for airfoils at non-zero angle of attack.
3209-3220
Gill, James R.
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
June 2015
Gill, James R.
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
Gill, James R., Zhang, Xin and Joseph, Phillip F.
(2015)
Single velocity-component modeling of leading edge turbulence
interaction noise.
Journal of the Acoustical Society of America, 137 (6), .
(doi:10.1121/1.4921547).
Abstract
A computational aeroacoustics approach is used to predict leading edge turbulence interaction noise for real airfoils. One-component (transverse), two-component (transverse and streamwise), and three-component (transverse, streamwise, and spanwise) synthesized turbulence disturbances are modeled instead of harmonic transverse gusts, to which previous computational studies of leading edge noise have often been confined. The effects of the inclusion of streamwise and spanwise disturbances on the noise are assessed. It is shown that accurate noise predictions can be made by modeling only transverse disturbances which reduces the computational expense of simulations. The accuracy of using only transverse disturbances is assessed for symmetric and cambered airfoils, and also for airfoils at non-zero angle of attack.
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Accepted/In Press date: 7 May 2015
e-pub ahead of print date: 19 June 2015
Published date: June 2015
Organisations:
Aeronautics, Astronautics & Comp. Eng
Identifiers
Local EPrints ID: 378723
URI: http://eprints.soton.ac.uk/id/eprint/378723
ISSN: 0001-4966
PURE UUID: 6344db81-78b8-45c5-88d3-0034aa6edbd9
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Date deposited: 20 Jul 2015 09:45
Last modified: 14 Mar 2024 20:27
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Author:
Xin Zhang
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