This work presents a comparative study of design and development, in addition, of analyses of variable span morphing of the tapered wing (VSMTW) for the unmanned aerial vehicle (UAV). The proposed concept consists in the sliding of the inner section into the fixed part along the wing with varying the angle of the inner section inside the fixed part (parallel with the leading edge and the moving-wing axis is coincident to the fixed-wing axis) within two configurations. The wing design is based on a NACA 4412 aerofoil with the root chord of 0.675m and the tip chord of 0.367m for the fixed segment and 0.320m for the moving segment. Morphing wing analysis occurs at three selected locations that have been specified for extending and modifying span length by (25%, 50%, and 75%) of its original length to fulfill various flight mission requirements. The main objective of this paper is to compare the aerodynamic characteristics for several span lengths and sweep angles and to find their most efficient combinations. The wing is optimised for different velocities during all phases of flight (min speed, loiter, cruise, and max speed) which are 17, 34, 51, and 68m/s, respectively. The analyses are performed by computing forces (drag and lift) and moments at various altitudes, such as at the sea level, at 5,000 and 10,000ft. Two-dimensional aerodynamic analyses are carried out using XFLR5 code, and the ANSYS Fluent solver is used for investigating the flow field on the three-dimensional wing structure. It has been observed that a variable span morphing of tapered wing technology with a variable sweep angle can deliver up to 32.93% improved aerodynamic efficiency. This concept design can also be used for the aircraft roll motion technique instead of conventional control devices. Furthermore, the range flight mission increases up to 46.89% when the wing is placed at its full length compared to an original position. Finally, it has been concluded from this study that the wing design is more sensitive to the changing angle of the inner section and more efficient in terms of aerodynamic characteristics.

中文翻译：

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变后掠角锥形机翼变展的比较与分析

这项工作对设计和开发进行了比较研究，此外，还对无人驾驶飞行器 (UAV) 的锥形机翼 (VSMTW) 的可变跨距变形进行了分析。所提出的概念包括将内部部分沿机翼滑入固定部分，改变固定部分内部的内部部分的角度（与前缘平行且动翼轴与固定翼轴重合） ) 在两种配置中。机翼设计基于 NACA 4412 翼型，根弦为 0.675m，固定段为 0.367m，移动段为 0.320m。变形机翼分析发生在三个选定位置，这些位置已指定用于将跨度长度延长和修改其原始长度的（25%、50% 和 75%）以满足各种飞行任务要求。本文的主要目的是比较几种跨距和后掠角的空气动力学特性，并找到它们最有效的组合。机翼针对飞行的所有阶段（最小速度、徘徊、巡航和最大速度）的不同速度进行了优化，分别为 17、34、51 和 68m/s。通过计算不同高度（例如海平面、5,000 和 10,000 英尺）的力（阻力和升力）和力矩来执行分析。二维气动分析采用XFLR5代码，ANSYS Fluent求解器用于研究三维机翼结构上的流场。据观察，具有可变后掠角的锥形机翼技术的可变跨度变形可以提高高达 32.93% 的空气动力学效率。这种概念设计也可用于飞机横滚运动技术，而不是传统的控制装置。此外，与原始位置相比，当机翼全长放置时，航程飞行任务增加了 46.89%。最后，从这项研究中得出结论，机翼设计对内部截面的变化角度更敏感，在空气动力学特性方面更有效。