Active flow control for aerofoils has been proven to be an effective way to improve the aerodynamic performance of aircraft. A conceptual hybrid design with surfaces embedded with Shape-Memory Alloy (SMA) and trailing Macro Fibre Composites (MFC) is proposed to implement active flow control for aerofoils. A Computational Fluid Dynamics (CFD) model has been built to explore the feasibility and potential performance of the proposed conceptual hybrid design. Accordingly, numerical analysis is carried out to investigate the unsteady flow characteristics by dynamic morphing rather than using classical static simulations and complicated coupling. The results show that camber growth by SMA action could cause an evident rise of Cl and Cd in the take-off/landing phases when the Angle-of-Attack (AoA) is less than 10°. The transient tail vibration behaviour in the cruise period when using MFC actuators is studied over wide ranges of frequency, AoA and vibration amplitude. The buffet frequency is locked in by the vibration frequency, and a decrease of 1.66–2.32% in Cd can be achieved by using a proper vibration frequency and amplitude.

中文翻译：

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基于形状记忆合金和粗纤维复合材料的主动流控翼型概念设计与数值研究

翼型主动流动控制已被证明是提高飞机气动性能的有效途径。提出了一种表面嵌入形状记忆合金 (SMA) 和尾随宏观纤维复合材料 (MFC) 的概念混合设计，以实现翼型的主动流动控制。已经建立了计算流体动力学 (CFD) 模型，以探索所提出的概念混合设计的可行性和潜在性能。因此，进行数值分析以通过动态变形而不是使用经典的静态模拟和复杂的耦合来研究非定常流动特性。结果表明，通过 SMA 作用的外倾角增长可能导致 C 的明显上升l和 Cd在迎角 (AoA) 小于 10° 时的起飞/着陆阶段。在很宽的频率、AoA 和振动幅度范围内研究了使用 MFC 执行器时巡航期间的瞬态尾部振动行为。抖振频率被振动频率锁定，C 下降 1.66-2.32%d可以通过使用适当的振动频率和振幅来实现。