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翼梢小翼能够抑制翼尖涡的形成,减小诱导阻力,增加航程。目前翼梢小翼的设计目标是改善飞机巡航阶段的升阻特性,而无法在起降、爬升阶段提供最优的减阻效果。本文设计了一种伸缩栅格结构变展长翼梢小翼,通过在飞行过程中控制翼梢小翼高度的变化,改善飞机起降、爬升阶段和巡航阶段的气动性能。利用基于涡格法的AVL软件计算伸缩式翼梢小翼对飞机气动性能的影响,结果表明在起降、爬升阶段(0.3Ma,8°迎角),这种伸缩式翼梢小翼能使升力系数提高0.21%,诱导阻力系数降低0.57%,而翼根弯矩系数仅增加0.06%,因此这种伸缩式翼梢小翼具有改善飞机起降和爬升性能的潜力。
Winglets can inhibit the formation of wingtip vortex, reduce induced resistance and increase range. At present, the design goal of the winglets is to improve the lift resistance characteristics of the aircraft during the cruise phase, but can not provide the optimal drag reduction effect during the take-off and landing phases. In this paper, we design an extended-wingtip with a retractable grid structure to improve the aerodynamic performance of the aircraft taking off and landing, climbing and cruising phases by controlling the winglet wing height during flight. The AVL software based on the vortex method is used to calculate the effect of the retractable winglets on the aerodynamic performance of the aircraft. The results show that the retractable winglets can make The lift coefficient increases by 0.21%, the induced drag coefficient decreases by 0.57%, and the root bending moment coefficient increases by only 0.06%. Therefore, this retractable winglets have the potential to improve the take-off and landing performance of the aircraft.