Prediction of helicopter rotor discrete frequency noise for three scale models

A new computer program that uses Farassat’s most advanced subsonic time domain formulation has been written to predict helicopter rotor discrete frequency noise. A brief description of the program (WOPWOP), is followed by a comparison of predicted and experimentally measured acoustic pressure and spectra for a 1/4 scale UH-1 model rotor blade and a 1/7 scale OLS (AH-1G) model rotor blade. The rotorcraft flight simulation computer program C81 was used to predict the spanwise loading on the rotor for aerodynamic input into the acoustic prediction. Comparisons are made for different flight conditions and microphone locations with good results. In general, the acoustic pressure is underpredicted. The acoustic predictions for a tapered rotor blade and predictions for microphones well below the tip path plane show less underprediction. Finally, in-plane motion of the rotor blade is shown to significantly affect the peak-to-peak amplitude of the acoustic pressure for high advancing tip Mach numbers.