受限於設備與實驗環境，風洞實驗難以還原飛行器於高雷諾數飛行時空氣動力表現。為此本研究旨在找出合適的觸發條(Trip Strip)尺寸以人為方式改變邊界層狀態，達到模擬高雷諾數流場之目的。
本研究對象為仿製NATO所開發之通用無人飛行載具SACCON(Stability and Control Configuration)的NCKU UCAV Model，以探討翼前緣觸發條高度與雷諾數變化對其渦流結構的關係。研究透過風洞進行。實驗內容為表面流場可視化、表面壓力量測以及升阻力量測。
結果顯示，裝有觸發條之模型，增強接觸流強度並使翼後緣處壓力升高，使模型於低攻角時能延後或避免流動分離現象。作為低雷諾數特徵之Inner Vortex因失去形成機制而消失。翼尖渦流受增強接觸流影響延後生成。觸發條高度變化造成渦流系統靠近翼前緣、渦流半徑增加以及渦流強度下降。而安裝觸發條使升力係數較光滑表面低，並且於渦流形成階段減少阻力係數。

Due to limitations of the experimental facilities , wind tunnel experiment is hard to simulate the aerodynamic condition at high Reynolds number. Therefore, this study aims to find an appropriate trip strip height to simulate the high Reynolds number condition.
This study focuses on the NCKU UCAV model, imitating the UCAV called Stability and Control Configuration or SACCON developed by NATO. The study investigates the relationship between leading-edge trip strip height, Reynolds number, and vortex structure. The experimental methods are oil film visualization, surface pressure measurement, and aerodynamic force measurement.
The results indicate that the trip strip enhances the attached flow and increases the pressure near the trailing-edge. Therefore, the flow delays or prevents flow separation at low angle of attack. The inner vortex, a characteristic of NCKU UCAV Model at low Reynolds number, vanishes due to the loss of formation mechanism. The wingtip vortex formation is delayed as a result of the strengthened attachment flow. With installation of trip strip, the vortex moves close to the leading-edge, resulting in increasing the radius of vortex and reducing the strength of vortex. Additionally, the installation of trip strips leads to a lower lift coefficient compared with a smooth surface and a reduction in drag coefficient in the vortex formation phase.

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