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Airfoil-gust interactions in transonic flow

Airfoil-gust interactions in transonic flow
Airfoil-gust interactions in transonic flow
Leading edge noise is a significant broadband noise source in aircraft engines, and is the primary broadband noise mechanism in outlet guide vane noise in turbofans, and broadband rotor wake interaction noise in contra-rotating open rotor engines. Previous authors have studied the effects of various aspects relating to this noise source, including airfoil geometry effects, cascade effects, and Mach number effects. However, previous literature has not addressed the effects on the noise due to locally supersonic regions that might be present in
the mean flow around the rotor blades. The current work uses computational aeroacoustic methods to investigate the effects of locally supersonic regions on the noise due to airfoil-gust interactions. An established computational aeroacoustics code has been extended to give stable predictions in supersonic regions with a localized artificial diffusivity method.
Initial results of a NACA 0012 airfoil in M = 0.8 flow interacting with oncoming vortical waves are shown, alongside results for a NACA 0006 airfoil in M = 0.5 flow at a 6 ? angle of attack. The changes to the noise and the underlying mechanisms are discussed for both cases, including additional noise sources caused by the supersonic region.
American Institute of Aeronautics and Astronautics
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Zhong, Siyang
414858d2-91b4-454c-957e-9280ed2e3a0f
Fattah, Ryu
658d0694-d683-4839-89a0-b95601ebe365
Angland, David
b86880c6-31fa-452b-ada8-4bbd83cda47f
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Zhong, Siyang
414858d2-91b4-454c-957e-9280ed2e3a0f
Fattah, Ryu
658d0694-d683-4839-89a0-b95601ebe365
Angland, David
b86880c6-31fa-452b-ada8-4bbd83cda47f

Gill, James, Zhang, Xin, Zhong, Siyang, Fattah, Ryu and Angland, David (2016) Airfoil-gust interactions in transonic flow. In 22nd AIAA/CEAS Aeroacoustics Conference : Aeroacoustics Conferences. American Institute of Aeronautics and Astronautics.. (doi:10.2514/6.2016-2872).

Record type: Conference or Workshop Item (Paper)

Abstract

Leading edge noise is a significant broadband noise source in aircraft engines, and is the primary broadband noise mechanism in outlet guide vane noise in turbofans, and broadband rotor wake interaction noise in contra-rotating open rotor engines. Previous authors have studied the effects of various aspects relating to this noise source, including airfoil geometry effects, cascade effects, and Mach number effects. However, previous literature has not addressed the effects on the noise due to locally supersonic regions that might be present in
the mean flow around the rotor blades. The current work uses computational aeroacoustic methods to investigate the effects of locally supersonic regions on the noise due to airfoil-gust interactions. An established computational aeroacoustics code has been extended to give stable predictions in supersonic regions with a localized artificial diffusivity method.
Initial results of a NACA 0012 airfoil in M = 0.8 flow interacting with oncoming vortical waves are shown, alongside results for a NACA 0006 airfoil in M = 0.5 flow at a 6 ? angle of attack. The changes to the noise and the underlying mechanisms are discussed for both cases, including additional noise sources caused by the supersonic region.

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Accepted/In Press date: 1 April 2016
e-pub ahead of print date: 30 May 2016
Published date: 30 May 2016
Venue - Dates: 22nd AIAA/CEAS Aeroacoustics Conference, France, 2016-05-30 - 2016-06-01
Organisations: Aeronautics, Astronautics & Comp. Eng

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Local EPrints ID: 396436
URI: https://eprints.soton.ac.uk/id/eprint/396436
PURE UUID: bee3ec30-9198-4cca-bb1e-1c9ce89f8e46

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Date deposited: 07 Jun 2016 15:52
Last modified: 13 Mar 2019 18:51

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Contributors

Author: James Gill
Author: Xin Zhang
Author: Siyang Zhong
Author: Ryu Fattah
Author: David Angland

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