無人飛行載具擁有低成本及高機動性之優點，已逐漸取代有航空器，民間應用於防災救災系統作更深入災區的偵蒐與監視。無人機執行任務時需要在低速度下完成工作，且必須維持飛行性能。本研究設計與製作無人飛行載具機翼之前緣翼條，使飛機在高升力需求時，利用機翼的前緣翼條(Slat)來提高最大升力及失速攻角，增進飛行安全並提高低速飛行性能。透過風洞實驗，翼表面的流場狀態以煙流法進行觀測翼面效應，探討前緣翼條未開啟與展開後之失速攻角性能差異，了解機翼空氣動力特性，並以六力平衡儀測得機翼的升力、阻力並計算升力、阻力係數。實驗室測試完成後，本研究更以實際飛行測試，來驗證前緣翼條對低速飛行性能的改善效果。

Unmanned aerial vehicles (UAV) have gradually replaced part of manned aircraft because of their advantages of low-cost and high maneuverability in civilian applications for reconnaissance, surveillance and information collection to support disaster rescue. In UAV missions, low speed operation is demanded with required performance. A wing with the leading-edge slat for UAV is designed and implemented in this study to increase the maximum lift and stall angle during low speed operations. Via the wind tunnel experiments, the flow properties on the wing surface were visualized and analyzed by the smoke flow method. The differences of stall angle when the slat works or not will be well investigated. In order to understand the aerodynamics properties, the lift and drag were measured by force balance and to calculate the coefficients of lift and drag. After laboratory observations, real flight tests were carried out to verify the actual performance in low speed operations.

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