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A numerical investigation of the airfoil-gust interaction noise in transonic flows: Acoustic processes

A numerical investigation of the airfoil-gust interaction noise in transonic flows: Acoustic processes
A numerical investigation of the airfoil-gust interaction noise in transonic flows: Acoustic processes

The sound produced by airfoil-gust interaction is a significant source of broadband noise in turbofan engines or contra-rotating open rotors (CRORs). There are competing mechanisms in this regime because of the presence of shocks that were seldom considered in the previous subsonic studies. A numerical investigation of airfoil-gust interaction noise at transonic speeds is undertaken in this work. By introducing vortical gust/synthetic turbulence to specified regions in the computational domain to interact with different elements in the flow field, it is shown that the dominant sound source is caused by leading edge-gust interaction. It is demonstrated that both streamwise and transverse disturbances interact with the near-field non-uniform mean flow and shocks can produce sound using a local gust injection method. The propagation of sound is significantly influenced by the presence of the shocks, and the far field radiation pattern is changed. We also study the effect of gust strength on the near and far field properties. The linearity is maintained for gust strength smaller than 1.0% of the mean flow velocity. Otherwise, the shocks may experience oscillations that will alter the near-field aerodynamics and far-field radiation.

Airfoil-gust interaction, Scattering, Shocks, Transonic flow
0022-460X
239-256
Zhong, Siyang
414858d2-91b4-454c-957e-9280ed2e3a0f
Zhang, Xin
8aeec26a-4702-4089-ba59-fdf0ca425c74
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Fattah, Ryu
b7fbaf19-132f-4a04-828e-6656b4d83f24
Sun, Yuhao
c44dd437-31ee-439e-b34e-9110612eeb6a
Zhong, Siyang
414858d2-91b4-454c-957e-9280ed2e3a0f
Zhang, Xin
8aeec26a-4702-4089-ba59-fdf0ca425c74
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Fattah, Ryu
b7fbaf19-132f-4a04-828e-6656b4d83f24
Sun, Yuhao
c44dd437-31ee-439e-b34e-9110612eeb6a

Zhong, Siyang, Zhang, Xin, Gill, James, Fattah, Ryu and Sun, Yuhao (2018) A numerical investigation of the airfoil-gust interaction noise in transonic flows: Acoustic processes. Journal of Sound and Vibration, 425, 239-256. (doi:10.1016/j.jsv.2018.04.010).

Record type: Article

Abstract

The sound produced by airfoil-gust interaction is a significant source of broadband noise in turbofan engines or contra-rotating open rotors (CRORs). There are competing mechanisms in this regime because of the presence of shocks that were seldom considered in the previous subsonic studies. A numerical investigation of airfoil-gust interaction noise at transonic speeds is undertaken in this work. By introducing vortical gust/synthetic turbulence to specified regions in the computational domain to interact with different elements in the flow field, it is shown that the dominant sound source is caused by leading edge-gust interaction. It is demonstrated that both streamwise and transverse disturbances interact with the near-field non-uniform mean flow and shocks can produce sound using a local gust injection method. The propagation of sound is significantly influenced by the presence of the shocks, and the far field radiation pattern is changed. We also study the effect of gust strength on the near and far field properties. The linearity is maintained for gust strength smaller than 1.0% of the mean flow velocity. Otherwise, the shocks may experience oscillations that will alter the near-field aerodynamics and far-field radiation.

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More information

Accepted/In Press date: 7 April 2018
e-pub ahead of print date: 13 April 2018
Published date: 7 July 2018
Keywords: Airfoil-gust interaction, Scattering, Shocks, Transonic flow

Identifiers

Local EPrints ID: 422419
URI: http://eprints.soton.ac.uk/id/eprint/422419
ISSN: 0022-460X
PURE UUID: 1c42aab5-1307-4ee3-8058-ff1cc019f2fb

Catalogue record

Date deposited: 23 Jul 2018 16:31
Last modified: 07 Oct 2020 00:27

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