Tiltwing aircraft achieve the transition between helicopter mode and cruise mode through the synchronous tilting of the wing and rotors, thereby combining vertical takeoff and landing capability with high-speed cruise performance. However, in helicopter mode, pronounced aerodynamic interference exists between the rotor wake and the wing, which adversely affects the overall aerodynamic performance of the aircraft. In this study, an unsteady numerical simulation methodology applicable to tiltwing aircraft operating in helicopter mode is established, with particular emphasis on investigating the effectiveness of flaperon deflection in alleviating such aerodynamic interference. The results indicate that appropriate flaperon deflection can mitigate the aerodynamic interaction between the wing and the rotor. Nevertheless, the flaperon deflection rate has a significant influence on the evolution of hub vortex structures; excessively high deflection rates may lead to vortex breakdown and anomalous pressure distributions, thereby degrading the effectiveness of flaperon deflection. The findings of this study provide useful guidance for selecting suitable flaperon deflection simulation strategies during the vertical takeoff and landing phase of tiltwing aircraft.
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