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Airframe Noise Prediction by Acoustic Analogy: RevisitedThe present work follows a recent survey of airframe noise prediction methodologies. In that survey, Lighthill s acoustic analogy was identified as the most prominent analytical basis for current approaches to airframe noise research. Within this approach, a problem is typically modeled with the Ffowcs Williams and Hawkings (FW-H) equation, for which a geometry-independent solution is obtained by means of the use of the free-space Green function (FSGF). Nonetheless, the aeroacoustic literature would suggest some interest in the use of tailored or exact Green s function (EGF) for aerodynamic noise problems involving solid boundaries, in particular, for trailing edge (TE) noise. A study of possible applications of EGF for prediction of broadband noise from turbulent flow over an airfoil surface and the TE is, therefore, the primary topic of the present work. Typically, the applications of EGF in the literature have been limited to TE noise prediction at low Mach numbers assuming that the normal derivative of the pressure vanishes on the airfoil surface. To extend the application of EGF to higher Mach numbers, the uniqueness of the solution of the wave equation when either the Dirichlet or the Neumann boundary condition (BC) is specified on a deformable surface in motion. The solution of Lighthill s equation with either the Dirichlet or the Neumann BC is given for such a surface using EGFs. These solutions involve both surface and volume integrals just like the solution of FW-H equation using FSGF. Insight drawn from this analysis is evoked to discuss the potential application of EGF to broadband noise prediction. It appears that the use of a EGF offers distinct advantages for predicting TE noise of an airfoil when the normal pressure gradient vanishes on the airfoil surface. It is argued that such an approach may also apply to an airfoil in motion. However, for the prediction of broadband noise not directly associated with a trailing edge, the use of EGF does not appear to offer any advantages over the use of FSGF at the present stage of development. It is suggested here that the applications of EGF for airframe noise analysis be continued. As an example pertinent to airframe noise prediction, the Fast Scattering Code of NASA Langley is utilized to obtain the EGF numerically on the surface of a three dimensional wing with a flap and leading edge slat in uniform rectilinear motion. The interpretation and use of these numerical Green functions are then discussed.
Document ID
20060013469
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Farassat, F. (NASA Langley Research Center Hampton, VA, United States)
Casper, Jay H. (NASA Langley Research Center Hampton, VA, United States)
Tinetti, A. (NCI Information Systems, Inc. United States)
Dunn, M. H. (National Inst. of Aerospace Hampton, VA, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2006
Subject Category
Acoustics
Report/Patent Number
AIAA Paper 2006-2564
Meeting Information
Meeting: 12th AIAA/CEAS Aeroacoustics Conference
Location: Cambridge, MA
Country: United States
Start Date: May 8, 2006
End Date: May 10, 2006
Sponsors: American Inst. of Aeronautics and Astronautics, National Oceanic and Atmospheric Administration
Funding Number(s)
OTHER: 23-781-10-33
Distribution Limits
Public
Copyright
Public Use Permitted.

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