LBM 해석을 이용한 회전익기 동체의 박리 유동 및 항력 특성 분석

초록

This study investigates the flow separation behavior on the upper and lower fuselage surfaces of a next-generation high-speed rotorcraft and its influence on drag characteristics using lattice Boltzmann Method (LBM) simulations. The LBM results were validated against wind-tunnel experiments. The analysis revealed that adverse pressure gradients induced massive flow separation on both the upper engine-cowling and lower ramp regions. Early separation occurred on the upper surface, whereas delayed separation appeared on the lower surface. The separated flows from these regions interacted in the aft fuselage, forming large-scale wake structures that hindered pressure recovery and consequently increased pressure drag. As the angle of attack increased, the separation point on the upper surface moved forward, while that on the lower surface shifted rearward, exhibiting opposite trend. These results provide fundamental insights for designing drag-reduction devices and optimizing fuselage configurations in future rotorcraft development

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