Abstract
In this Paper, the noise generated from the 30P30N high-lift airfoil is simulated with a high-order spectral difference solver. In the simulation, the inflow Mach number is 0.17, and the Reynolds number based on the inflow velocity and the chord length of the airfoil is . Three angles of attack, which are 4, 5.5, and 8.5 deg, are computed. The time-averaged mean flow fields are compared with the experimental data, which include the velocity and spanwise vorticity profiles in the shear layer of the slat cove, the pressure coefficients on the surface of the airfoil. The dynamic pressure on the surface of the slat is sampled and compared with the experimental data by other researchers, and a good agreement is obtained. The far-field noise spectra, computed with the permeable Ffowcs Williams–Hawkings integration method, also agree well with the experimental data. The tone noise source is studied by analyzing the correlation between the dynamic pressure on the slat cove surface and the near-field noise. It is found that the tone noise is strongly correlated with the dynamic pressure close to the reattachment point on the slat cove surface.
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