本研究概念構想是以NASA M6機翼模組為為機翼主架構，探討飛機的飛行特性，本研究變更機翼掠角成為前掠型機翼，並設定該機翼為可變式機構，機翼可由前掠翼轉動變成三角翼，期能結合兩種機翼翼型特點。在飛機起飛或降落時使用前掠翼翼型增加升力，降低機場跑道最小起降範圍，另外在高速巡航時可轉換成三角翼翼型降低阻力，降低油耗增加巡航距離，提升飛機操控性能，並改善前掠型機翼高速時產生之離散效應。本研究將藉由設計3D機翼模組並運用數值分析軟體CFX對該機翼之氣動佈局進行計算，分析機翼在相同設定風速及密度等環境參數，不同角度下承受的升阻力之變化，藉以驗證可變式前掠型機翼效益。另本次研究僅針對機翼外型承受升、阻力及彎矩變化探討，其結構分析及轉動機構設計將不在本研究探討分析。

This study uses the NASA M6 wing module as the wing main structure to investigate the airfoil performance. By changing the wing sweep angle from forward swept wing into Delta wing. In theory,one can combine the strength of these two airfoils to enhance the aircraft performance. The forward swept wing can increase lift while takes off or lands, which can also reduce the minimum landing range of the airport runway. As for the delta wing, it can reduce drag and fuel consumption to increase cruising distance at high speed and can also improve the discrete effect that forward swept wing would generate while in high speed.
This study uses the numerical analysis software CFX to simulate the numerical results. Based on the design of the 3D wing module, we calculate the aerodynamic layout of the wing and analyze the changes of dragin different wing rotating angles under the same setting of wind speed and density and other environmental parameters. Furthermore, we verify the effectiveness of the variable forward swept wing. Inthis study,we will discussthe change on lift, drag and bending moment of the wing configuration to understand the aircraft performance. Structural analysis and the design of the rotating mechanism will not be discussed in this study.

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