The University of Southampton
University of Southampton Institutional Repository

Attenuation of slat trailing edge noise using acoustic liners

Attenuation of slat trailing edge noise using acoustic liners
Attenuation of slat trailing edge noise using acoustic liners
Noise generated by high-lift devices such as the slats on the leading edge of a wing is a major contributor to the overall airframe noise during the landing approach of a commercial aircraft. In this work the concept of attenuating noise sources located at the trailing edge of a slat using absorptive acoustic liners in the slat gap is explored using a time-domain computational aeroacoustic (CAA) scheme. The aim of the computational modelling is to demonstrate the feasibility of controlling slat noise using acoustic liners, and to optimize the design for a future experiment. A model scale three-element high-lift airfoil is modelled; the slat and flap deflection angles are 23 deg and 32 deg respectively and the slat has a blunt trailing edge. The freestream Mach number is 0.2 and the main element angle of attack is 5 deg, corresponding to a typical approach condition. The Reynolds number is 3.6 million, based on the airfoil chord with the high-lift devices retracted.
The computational results are divided into three parts: (1) an unsteady Reynolds-Averaged Navier-Stokes (URANS) simulation using high-order spatial and temporal schemes is conducted for a wing without acoustic liners; the computed flow shows the presence of vortex shedding and acoustic sources behind the slat trailing edge; (2) a calculation of the radiated sound field is made for a range of liner impedance values by solving the linearised Euler equations (LEE) for a modelled acoustic source located at the trailing edge of the slat; (3) URANS computations for the wing with liner treatment are conducted. The results show that acoustic liners on the slat cove and on the main element can provide useful attenuation of slat trailing edge noise.
1475-472X
311-333
Ma, Zhaokai
655d38b8-1756-4908-a522-291cf5a642a0
Smith, Malcolm G.
1bc8608d-0178-4793-8f73-46a6c6b9b279
Richards, Simon K.
61047422-678e-4800-a032-b874a987cb75
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421
Ma, Zhaokai
655d38b8-1756-4908-a522-291cf5a642a0
Smith, Malcolm G.
1bc8608d-0178-4793-8f73-46a6c6b9b279
Richards, Simon K.
61047422-678e-4800-a032-b874a987cb75
Zhang, Xin
3056a795-80f7-4bbd-9c75-ecbc93085421

Ma, Zhaokai, Smith, Malcolm G., Richards, Simon K. and Zhang, Xin (2006) Attenuation of slat trailing edge noise using acoustic liners. International Journal of Aeroacoustics, 5 (4), 311-333. (doi:10.1260/147547206779379886).

Record type: Article

Abstract

Noise generated by high-lift devices such as the slats on the leading edge of a wing is a major contributor to the overall airframe noise during the landing approach of a commercial aircraft. In this work the concept of attenuating noise sources located at the trailing edge of a slat using absorptive acoustic liners in the slat gap is explored using a time-domain computational aeroacoustic (CAA) scheme. The aim of the computational modelling is to demonstrate the feasibility of controlling slat noise using acoustic liners, and to optimize the design for a future experiment. A model scale three-element high-lift airfoil is modelled; the slat and flap deflection angles are 23 deg and 32 deg respectively and the slat has a blunt trailing edge. The freestream Mach number is 0.2 and the main element angle of attack is 5 deg, corresponding to a typical approach condition. The Reynolds number is 3.6 million, based on the airfoil chord with the high-lift devices retracted.
The computational results are divided into three parts: (1) an unsteady Reynolds-Averaged Navier-Stokes (URANS) simulation using high-order spatial and temporal schemes is conducted for a wing without acoustic liners; the computed flow shows the presence of vortex shedding and acoustic sources behind the slat trailing edge; (2) a calculation of the radiated sound field is made for a range of liner impedance values by solving the linearised Euler equations (LEE) for a modelled acoustic source located at the trailing edge of the slat; (3) URANS computations for the wing with liner treatment are conducted. The results show that acoustic liners on the slat cove and on the main element can provide useful attenuation of slat trailing edge noise.

This record has no associated files available for download.

More information

Published date: 2006

Identifiers

Local EPrints ID: 38944
URI: http://eprints.soton.ac.uk/id/eprint/38944
ISSN: 1475-472X
PURE UUID: 2dfa4f32-e577-4283-8e50-fe5125c8f6fe

Catalogue record

Date deposited: 16 Jun 2006
Last modified: 15 Mar 2024 08:08

Export record

Altmetrics

Contributors

Author: Zhaokai Ma
Author: Malcolm G. Smith
Author: Simon K. Richards
Author: Xin Zhang

Download statistics

Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.

View more statistics

Atom RSS 1.0 RSS 2.0

Contact ePrints Soton: eprints@soton.ac.uk

ePrints Soton supports OAI 2.0 with a base URL of http://eprints.soton.ac.uk/cgi/oai2

This repository has been built using EPrints software, developed at the University of Southampton, but available to everyone to use.

We use cookies to ensure that we give you the best experience on our website. If you continue without changing your settings, we will assume that you are happy to receive cookies on the University of Southampton website.

×