Aeroacoustics performance is assessed for three conceptual low-noise and high-lift wings using the surface integral methods of acoustic analogy, including the Kirchhoff method, the Ffowcs Williams and Hawkings method and the Curie method. A new way is proposed to define the integral surface that encloses the core flow region for the first two methods on the basis of the vorticity magnitudes. Both of the first two methods are used to compute the noise generated by the core region of the flow, which is responsible for most of the noise generation. The results obtained by the FWH method support those given by the Kirchhoff method. The Curie analogy approach is adopted to calculate the noise by the boundary layer flow attached on the walls inside the core flow region. Through comparison of the results of the three approaches, the levels of the contribution to the noise by the volume flow and the boundary layers are studied for the configurations. Finally, the mechanism of efficiency on the noise reduction is presented for the three configurations.
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