A Study of Helicopter Rotor Rotational Noise

Abstract

The rotational noise of model helicopter rotors in forward flight was studied in an anechoic wind tunnel. The parameters under study were the rotor thrust (blade loading), blade number, and advance ratio. The separate effects of each parameter were identified with the other parameters being held constant. The directivity of the noise was also measured. Twelve sets of data for rotational noise as a function of frequency were compared with the theory of Lowson and Ollerhead. In general, the agreement is reasonably good, except for the cases of 1) low and high disk loadings, 2) the four-bladed rotor, and 3) low advance ratios. The theory always underestimates the rotational noise at high harmonics.