Acoustic Analysis of Electric Ducted Fans
Abstract
A selected reversed engineered fan was investigated in order to predict fan noise, thrust and torque during hover flight. A sensitivity study was completed to determine fan noise at different configurations with 4, 8, 16, 24 and 36 fans, respectively. The analysis resulted in the selection of a 24-fans configuration for the Manta UAV, with 31 rotor blades per fan. A further increase of number of rotors from 31 to 40 would result on a noise reduction of 3 dB. Analytical predictions estimated a SPL of 108.1 dB for the first harmonic, while CFD predicted a SPL of 107.7 dB, providing a validation of the CFD model. In addition, the same CFD approach and methods used on Manta UAV were applied to the NASA rotor 67, showing that numerical results agree with the performance data. The CFD results showed that the rotor-stator geometry did not produce the required thrust, as initially used for the design. This difference could be a result of the degree of separation occurring on the rotor. It is concluded that the degree of flow separation could potentially be corrected by increasing the stagger angle of the rotor.
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