동축반전 복합형 회전익기 동체-푸셔 프로펠러 공력 간섭 현상에 관한 전산 해석

초록

A compound helicopter with coaxial main rotor and pusher propeller has been attracting much attention due to its long-range cruise and high-speed capability. However, the wake flow from the coaxial hub system and fuselage directly affects the inflow condition on the pusher propeller during high-speed flight. This study investigated the effects of hub system and fuselage wake structures on the aerodynamics of pusher propeller using high-fidelity lattice-Boltzmann method(LBM) simulation. The validation study of the LBM simulation against the measurements on the ROBIN fuselage model predicts the surface pressure coefficients on the fuselage at different locations. In this study, a geometry similar to the Sikorsky-Boeing SB>1 Defiant model is considered. The simulation results showed that the complex wake structure generated from the hub system and fuselage results in a decrease in the inflow velocity, thus leading to increase in the effective angle of attack of the pusher propeller blades. Moreover, thrust fluctuations of the pusher propeller were observed due to the ingestion of highly unsteady inflow into the pusher propeller. It was concluded that the simulation results provide significant insights into the flow physics occurring around the hub system, fuselage, and pusher propeller in high-speed forward flight conditions.

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