Russo, N.; Marano, A.D.; Gagliardi, G.M.; Guida, M.; Polito, T.; Marulo, F. Thrust and Noise Experimental Assessment on Counter-Rotating Coaxial Rotors. Aerospace2023, 10, 535.
Russo, N.; Marano, A.D.; Gagliardi, G.M.; Guida, M.; Polito, T.; Marulo, F. Thrust and Noise Experimental Assessment on Counter-Rotating Coaxial Rotors. Aerospace 2023, 10, 535.
Russo, N.; Marano, A.D.; Gagliardi, G.M.; Guida, M.; Polito, T.; Marulo, F. Thrust and Noise Experimental Assessment on Counter-Rotating Coaxial Rotors. Aerospace2023, 10, 535.
Russo, N.; Marano, A.D.; Gagliardi, G.M.; Guida, M.; Polito, T.; Marulo, F. Thrust and Noise Experimental Assessment on Counter-Rotating Coaxial Rotors. Aerospace 2023, 10, 535.
Abstract
Multirotors are gaining great importance in the layout of innovative and more agile mobility. In this framework, a possible solution to developing an aircraft complying with the stringent size requirements characterizing this type of application can be a coaxial rotor configuration. To exploit the several possibilities linked to coaxial rotors, a scaled experimental model is designed to evaluate the performances of the counter-rotating propellers system, concerning the distance between the two propellers. Both thrust and noise are considered as parameters of interest. Two brushless motors are deployed whereas the propellers' angular velocity, in terms of round per minute (rpm), is controlled by an external control system. Tests are conducted on both single isolated propellers as well as on the counter-rotating system: the two propellers and their respective motors have been characterized concerning the thrust. Furthermore, a comparison with a numerical model is performed. Noise evaluation on the single propeller has shown a motor contribution prevalence at a low rpm regime (1140-1500 rpm) and a propeller prevalence for angular velocities higher than 1860 rpm. By varying the distances between the propellers a sensitivity analysis is performed with the aim of identifying the optimum configuration taking into account both noise and thrust performances.
Copyright:
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