블레이드 매수에 따른 로터-에어프레임 공력 소음 저감 연구

초록

For next-generation rotorcraft based on distributed electric propulsion (DEP) systems, complex aerodynamic interactions occur between the wakes generated by high disk loading rotors and airframe components. In particular, the airframe connecting the rotor to the fuselage is periodically immersed in the rotor wake, inducing strong aerodynamic interactions and acting as a significant noise source. This study analyzed the aerodynamic and acoustic characteristics of the rotor-airframe interaction in hover using a coupled source-doublet panel method and unsteady vortex particle method. The results showed that the interaction induced periodic fluctuations in rotor aerodynamic loads, as well as vibration-driven unsteady loads on the airframe due to wake interaction. Subsequently, intense tonal noise generated by these vibration-induced pressure fluctuations on the airframe was predicted using the Ffowcs Williams-Hawkings (FW-H) acoustic analogy. In addition, the effect of blade number on the reduction of loading noise was examined.

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