A Comparison of Multicopter Noise Characteristics with Increasing Number of Rotors
Brendan Smith, Gandhi, Niemiec
Abstract
This study examines the acoustic behavior in hover of manned-size, multi-rotor, eVTOL aircraft in the classical quadcopter, hexacopter and octocopter configurations. The rotors are assumed to have collective pitch control and operate at a specified RPM, with orthogonal and tip-to-tip rotor phasing considered. All configurations have the same disk loading and tip Mach number, with the rotor radius decreasing and RPM increasing, going from the quadcopter to the octocopter. The simulations use the Rensselaer Multicopter Analysis Code (RMAC) for the aerodynamic loads on the blades, coupled to PSU-WOPWOP for predictions of propagated noise. From the simulation results, orthogonal phasing between rotors is shown to produce significant noise reductions along inter-boom bisectors (between 9-14 dB relative to an equivalent single rotor, at 6lb/ft2 disk loading and 0.51 tip Mach number). Further reducing the tip Mach number not only reduces the propagated noise but produces even deeper regions of quiet along the inter-boom bisectors (18-25 dB quieter at 3lb/ft2 with 0.36 tip Mach number). An examination of the overall sound pressure frequency spectra indicates that smaller faster spinning rotors (going from the quadcopter to octocopter) produce more tonal peaks at higher frequencies which results in penalties in A-weighted noise.