The paper presents a method to find an optimal airfoil shape for the lowest trailing-edge noise level. In the present paper, the airfoil trailing edge geometry is modified from a baseline airfoil using a high-order polynomial function, which makes a concave trailing edge. In particular, three design parameters are employed to change the trailing-edge shape. The XFOIL is used to predict the aerodynamic performance and provide the input parameters to an empirical wall-pressure spectrum model. A predictive method that combines the empirical wall-pressure spectrum model with a diffraction model is used for the prediction of airfoil trailing-edge noise. A design optimization framework using the Kriging surrogate model and the Genetic algorithm is developed, which is used to find the optimum solution for airfoil geometry that minimizes trailing-edge noise and simultaneously improves the aerodynamic performance. The optimized results are validated using the numerical method. It is found that the trailing-edge noise level of an optimized airfoil is significantly reduced while improving the lift-to-drag ratio in comparison with the baseline NACA0012 airfoil.
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