Direct numerical simulations of noise generated by airfoil trailing edges
Direct numerical simulations of noise generated by airfoil trailing edges
Direct numerical simulations (DNS) are conducted of flow past a NACA-0012 airfoil
at various angles of attack.
The aim is to directly compute both the near-field hydrodynamics and the far-field
sound. The DNS data can then be used to investigate whether
the approach of determining the noise radiation based on the surface pressure
difference, as done in the classical trailing edge theory of Amiet,
yields satisfactory results for finite thickness airfoils subject to mean loading effects.
In addition, the accuracy of Amiet's surface pressure jump function is evaluated.
Overall, the modified theory of Amiet appears to be suitable for finite thickness airfoils.
However, Amiet's response function is not able to correctly predict the scattered pressure field
for cases where large vortices pass the trailing edge.
Moreover, predicting the airfoil self noise based only on the surface pressure difference appears not to
be applicable for all frequencies at higher angles of attack because the radiated sound is
only partly due to classical trailing edge noise mechanisms.
Sandberg, Richard D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Jones, Lloyd E.
f1da2878-d03c-4932-96a7-8058dfead381
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
2007
Sandberg, Richard D.
41d03f60-5d12-4f2d-a40a-8ff89ef01cfa
Jones, Lloyd E.
f1da2878-d03c-4932-96a7-8058dfead381
Sandham, Neil D.
0024d8cd-c788-4811-a470-57934fbdcf97
Joseph, Phillip F.
9c30491e-8464-4c9a-8723-2abc62bdf75d
Sandberg, Richard D., Jones, Lloyd E., Sandham, Neil D. and Joseph, Phillip F.
(2007)
Direct numerical simulations of noise generated by airfoil trailing edges.
13th CEAS/AIAA Aeroacoustics Conference (28th AIAA Aeroacoustics Conference), Rome, Italy.
20 - 22 May 2007.
15 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
Direct numerical simulations (DNS) are conducted of flow past a NACA-0012 airfoil
at various angles of attack.
The aim is to directly compute both the near-field hydrodynamics and the far-field
sound. The DNS data can then be used to investigate whether
the approach of determining the noise radiation based on the surface pressure
difference, as done in the classical trailing edge theory of Amiet,
yields satisfactory results for finite thickness airfoils subject to mean loading effects.
In addition, the accuracy of Amiet's surface pressure jump function is evaluated.
Overall, the modified theory of Amiet appears to be suitable for finite thickness airfoils.
However, Amiet's response function is not able to correctly predict the scattered pressure field
for cases where large vortices pass the trailing edge.
Moreover, predicting the airfoil self noise based only on the surface pressure difference appears not to
be applicable for all frequencies at higher angles of attack because the radiated sound is
only partly due to classical trailing edge noise mechanisms.
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More information
Published date: 2007
Additional Information:
AIAA 2007-3469
Venue - Dates:
13th CEAS/AIAA Aeroacoustics Conference (28th AIAA Aeroacoustics Conference), Rome, Italy, 2007-05-20 - 2007-05-22
Organisations:
Aerodynamics & Flight Mechanics
Identifiers
Local EPrints ID: 46240
URI: http://eprints.soton.ac.uk/id/eprint/46240
PURE UUID: 99a0d773-0781-4b9b-836b-5a6e38314196
Catalogue record
Date deposited: 06 Jun 2007
Last modified: 08 Jan 2022 02:49
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Contributors
Author:
Richard D. Sandberg
Author:
Lloyd E. Jones
Author:
Neil D. Sandham
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