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Scattering of landing gear noise by a wing

Scattering of landing gear noise by a wing
Scattering of landing gear noise by a wing
This paper describes a model of the scattering of landing gear noise for components installed under the wing of an aircraft or on a dummy wing in a wind tunnel experiment. The scattering surface of the wing is idealized as a flat two-dimensional rigid strip, and individual landing gear components are replaced by point monopole sources. The three part boundary value problem of scattering of plane waves by a strip has been solved previously using the Wiener-Hopf technique. The exact solution obtained via this procedure cannot be evaluated in closed form but it can be be approximated well in the farfield in terms of a primary scattered field, consisting of the sum of the fields diffracted by each edge independently in the absence of the other edge, and a so-called “edge interaction” term. The existing solution for plane wave incidence is here generalized to the problem of scattering of a monopole field by a rigid strip. A multiple-source directivity function is defined for calculating the effective directivity of landing gear noise as it would be measured under an aircraft wing. Further considerations pertinent to the extension of the present solution to the case of uniform flow are presented.
Carrilho, J.
b8e17e29-52b1-46f2-87a4-ec7da7ce31b7
Smith, M.
1bc8608d-0178-4793-8f73-46a6c6b9b279
Carrilho, J.
b8e17e29-52b1-46f2-87a4-ec7da7ce31b7
Smith, M.
1bc8608d-0178-4793-8f73-46a6c6b9b279

Carrilho, J. and Smith, M. (2008) Scattering of landing gear noise by a wing. Proceedings of the 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference). 05 - 07 May 2008. 12 pp .

Record type: Conference or Workshop Item (Paper)

Abstract

This paper describes a model of the scattering of landing gear noise for components installed under the wing of an aircraft or on a dummy wing in a wind tunnel experiment. The scattering surface of the wing is idealized as a flat two-dimensional rigid strip, and individual landing gear components are replaced by point monopole sources. The three part boundary value problem of scattering of plane waves by a strip has been solved previously using the Wiener-Hopf technique. The exact solution obtained via this procedure cannot be evaluated in closed form but it can be be approximated well in the farfield in terms of a primary scattered field, consisting of the sum of the fields diffracted by each edge independently in the absence of the other edge, and a so-called “edge interaction” term. The existing solution for plane wave incidence is here generalized to the problem of scattering of a monopole field by a rigid strip. A multiple-source directivity function is defined for calculating the effective directivity of landing gear noise as it would be measured under an aircraft wing. Further considerations pertinent to the extension of the present solution to the case of uniform flow are presented.

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More information

Published date: May 2008
Additional Information: Paper Number: AIAA-2008-2965
Venue - Dates: Proceedings of the 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference), 2008-05-05 - 2008-05-07

Identifiers

Local EPrints ID: 57788
URI: https://eprints.soton.ac.uk/id/eprint/57788
PURE UUID: d1555c22-be99-49c3-95f9-c952c9bc4e17

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Date deposited: 20 Aug 2008
Last modified: 13 Mar 2019 20:33

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