Airfoil noise induced by low-Mach-number flow is usually computed using the hybrid method, in which usually the incompressible Navier–Stokes equations are first solved to obtain the noise source and then acoustic analogy is used to predict the far-field noise. However this method is only suitable for predicting the aerodynamic noise in the long wavelength limit due to the loss of the acoustic component obtained from the incompressible flow simulation. The current paper presents an acoustic pressure correction method to predict the airfoil noise generated from low-Mach-number flow using a combination of acoustic analogy and the boundary element method. In order to validate the present method, the noise radiated from the low-Mach-number flow over an NACA0012 airfoil is predicted. Directivity patterns of the calculated noise at different frequencies have good agreement with those of the analytical solutions of Howe’s trailing-edge model.
Prediction of airfoil noise induced by low-Mach-number flow
2012-05-01
13 pages
Article (Journal)
Electronic Resource
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Prediction of airfoil noise induced by low-Mach-number flow
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