A Computational Study on the Aeroacoustics of a Multi-Rotor Unmanned Aerial System

The noise generated by a quadrotor biplane unmanned aerial system (UAS) is studied computationally for various conditions in terms of the UAS pitch angle, propellers rotating velocity (RPM), and speed to understand physics involved its aeroacoustics structure-borne noise. k-ω SST turbulence model Ffowcs Williams-Hawkings equations are used solve flow acoustics fields, respectively. sound pressure level measured using circular array microphones positioned around UAS, as well at specific locations on structure. local detect sources evaluate fluctuation surface. This study found that increases with angle propellers’ velocity, but it shows an irregular trend vehicle speed. major source from their interactions each other small angle. propeller CRC-3 structure interaction contributes large results also showed impose unsteadiness through two-way mechanism, resulting structure-born noises which depend RPM,