A Study on high-order numerical methods for aerodynamic noise prediction of helicopter blades in hovering flight

Abstract

Aero-Acoustics in far-field with the permeable methodology was applied to predict the aerodynamic noise according to the numerical schemes. A grid system was constructed by using overlapped grid method. The present high-order numerical method was coupled with the acoustic analogy using the Kirchhoff approach to Ffowcs Williams and Hawkings equations. Multi permeable surfaces surrounding the blades were constructed to include the flow noise generated from the shock waves and the tip vortices. The high speed impulsive noise on UH-1H rotor blades in hovering flight was predicted and compared with the experimental data.