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Abstract

This work deals with the numerical prediction of the trailing edge noise from rotating blades. A semi-empirical model of the wall pressure spectrum in proximity of the trailing edge is used in connection with an analytical flat-plate aerodynamic response function to compute the acoustic pressure fluctuations on the surface of the blade. Pressure signals with a broadband spectral content are generated by superimposing Fourier components of the blade pressure waves with a stochastic phase distribution. Finally, the far-field noise is computed through a numerical integration of the Ffowcs-Williams and Hawkings equation in the time domain. The hybrid analytical/numerical broadband noise prediction method is verified by computing the trailing-edge noise from a flat plate and comparing its spectrum to the one obtained through a direct analytical extrapolation of the wall pressure spectrum in the frequency domain. The same flat-plate results are then validated against measurements of trailing edge noise spectrum from a NACA-0012 airfoil. The method is finally used to compute the broadband noise from an aircraft propeller and results are compared with analytical results obtained through a blade strip approach. The method and the results described in this paper have been presented at the 14th CEAS-ASC workshop held on 7–8 October 2010 at the Institute of Aviation in Warsaw, Poland.

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Hybrid Analytical/Numerical Prediction of Propeller Broadband Noise in the Time Domain

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