Aircraft engine noise scattering by fuselage and wings: a computational approach

The paper presents a time-domain method for computation of sound radiation from aircraft engine sources to the far field. The effects of non-uniform flow around the aircraft and scattering of sound by fuselage and wings are accounted for in the formulation. The approach is based on the discretizatio...

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Bibliographic Details
Published in:Journal of sound and vibration 2003-05, Vol.263 (2), p.319-333
Main Authors: Stanescu, D., Hussaini, M.Y., Farassat, F.
Format: Article
Language:English
Subjects:
Acoustics
Aeroacoustics and atmospheric sound
Aeroacoustics, atmospheric sound
Aircraft Propulsion And Power
Computational techniques
Exact sciences and technology
Finite-element and galerkin methods
Fundamental areas of phenomenology (including applications)
Mathematical methods in physics
Physics
Structural acoustics and vibration
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Summary:The paper presents a time-domain method for computation of sound radiation from aircraft engine sources to the far field. The effects of non-uniform flow around the aircraft and scattering of sound by fuselage and wings are accounted for in the formulation. The approach is based on the discretization of the inviscid flow equations through a collocation form of the discontinuous Galerkin spectral element method. An isoparametric representation of the underlying geometry is used in order to take full advantage of the spectral accuracy of the method. Large-scale computations are made possible by a parallel implementation based on message passing. Results obtained for radiation from an axisymmetric nacelle alone are compared with those obtained when the same nacelle is installed in a generic configuration, with and without a wing.
ISSN:0022-460X
1095-8568
DOI:10.1016/S0022-460X(02)01126-4