Edge-source acoustic Green's function for an airfoil of arbitrary chord, with application to trailing-edge noise

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Wall-Pressure Spectral Model Including the Adverse Pressure Gradient Effects (2012, background): “Knowing the wall-pressure spectrum in the vicinity of the trailing edge and assuming an attached flow, the noise radiated as boundary layer vorticity is convected past the trailing edge of an airfoil and can be predicted using analytical models [1,3].”
Trailing-edge noise reduction using derivative-free optimization and large-eddy simulation (2007, background): “In the analysis of Howe (2001), the effect of a finite chord on the noise spectrum level was found to be significant when kC 2.5, where k = Mω is the acoustic wavenumber, or when ω 2.5/MC.”
Convective effects and the role of quadrupole sources for aerofoil aeroacoustics (2012, background): “Several analytical formulations for trailing-edge noise prediction use information on wall-pressure PSD collected in the trailing-edge region (Amiet 1976; Howe 1978, 2001; Roger & Moreau 2005; Moreau & Roger 2009).”
Extensions and limitations of analytical airfoil broadband noise models (2010, unknown): “They are derived in the reference papers for a stationary rectangular airfoil in a uniform flow and a reference taken at mid chord.”