Numerical simulation of the noise from the 30P30N highlift airfoil with spectral difference method

In this study the noise generated from the 30P30N highlift airfoil is simulated with a high order spectral difference code. In this 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 1.7 million. Three attack angles, which are 4, 5.5 and 8.5 degrees respectively, are simulated. The time averaged mean flow field, including the velocity profiles in the slat cove, the pressure coefficients on the surface of the airfoil, is presented and compared with the experimental data. 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, computed with the permeable Ffowcs Williams-Hawkings (FW-H) integration method, is presented and compared with the experimental data, and a good agreement is obtained. The tone noise source is analyzed with a coherence analysis of the dynamic pressure between the slat surface and the near field.