Resolvent Method Surface Pressures for Airfoil Trailing-Edge Noise Prediction

Abstract

We present the first resolvent method-based prediction of airfoil trailing-edge noise. Said noise prediction is obtained by using resolvent method pressure predictions as input to Amiet's theory. This framework is tested by comparing the noise prediction to results obtained from using DNS data as input to Amiet's theory. We subsequently analyse whether the resolvent method predicts the incident, scattered or total pressure field, to establish which expression of Amiet's theory to use. The resolvent method is found to capture the total pressure field, even accounting for the interaction of the incident and scattered pressure fields. The analysis is conducted for an acoustically sharp NACA0012 airfoil at zero incidence, and marks an exciting step in the development of a low-cost, physics-driven, hybrid computational aeroacoustics approach.