Numerical Analysis of Airfoil Trailing-Edge Noise for Straight and Serrated Edges at Incidence

The goal of this paper is to perform a detailed analysis the hydrodynamic near field and acoustic far NACA 64-618 airfoil with without serrations. impact serrations investigated across different angles attack serration flap angles. natural boundary-layer transition cases 6 7 AIAA Benchmark Problems for Airframe Noise Computations V Workshop Category 1 are considered as benchmark straight edge cases. numerical simulations performed using fully explicit, transient, compressible lattice Boltzmann equation implemented in computational fluid dynamics/computational aero-acoustics (CFD/CAA) solver SIMULIA PowerFLOW®. obtained by Ffowcs-Williams Hawkings integral solution applied surface. A mesh resolution study on trailing-edge demonstrate grid independence solution. results compare favorably against experimental data. angle effectiveness sawtooth reducing noise considering three It found that primarily affects reduction through modification 1) effective at which turbulent structures convected over serrated edge; 2) convection velocity spanwise coherence length along serration; 3) intensity wall-pressure fluctuations scattered edge. first last phenomena expected play most important role far-field reduction.