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A flow around NACA0012 wingtip is solved using a zonal LES/RANS hybrid method in order to understand the noise generation mechanism around the flap-edge. It is known from the previous studies that the flow around the blunt wingtip is similar to that of the flap-edge. Grid dependency studies are performed for both timeaveraged and unsteady components and the results are assessed by comparing with the experimental data. It became apparent that zonal LES/RANS hybrid results are more sensitive to the chordwise grid resolution, compared with that of RANS. Using the validated data, the noise generation mechanism around the wingtip is discussed. The near-field flow structures relevant to noise generation are obtained successfully.

Noise Simulation around NACA0012 Wingtip using Large Eddy Simulation