Prediction of Airfoil Trailing-Edge Noise Using Empirical Wall-Pressure Spectrum Models

This paper presents the predictions of airfoil turbulent boundary-layer trailing-edge noise using empirical wall-pressure spectrum models. Five empirical wall-pressure spectrum models were used. Input parameters for the wall-pressure spectrum models were obtained using the XFOIL panel code. A diffraction model was used to predict trailing-edge noise based on the empirically determined wall-pressure spectrum. This predictive method provided a fast evaluation of trailing-edge noise for arbitrary airfoil shapes with minimum flow input data. In total, 15 cases, including NACA 0012, DU96-W-180, NACA 64-418, and NACA 64-618 airfoils, were used to validate the trailing-edge noise prediction. Overall, it was found that one recently developed empirical wall-pressure spectrum model, named Lee’s model, provided the closest match with the measurement data. The detailed capabilities and limitations of each empirical wall-pressure spectrum model are discussed in terms of trailing-edge noise predictions.