本論文的動機在研究環流控制翼(Circulation Control Wing, CCW) 的應用。主要利用風洞實驗方法，前拉式螺旋槳動推力來控制上表面環流的流速，以獲得升力的提增，此種環流控制的方式稱之為上翼面噴流(Upper Surface Blowing, USB)。本實驗分別為以MH78為主翼剖面的矩形翼、半環形翼及環形翼三種翼模型做比較，探討其在低展弦比(AR=1)、低雷諾數下的無動力裝置時、升力及阻力值等基本空氣動力特性後，再以半環形翼及環形翼裝上動力組，亦進行風洞測試在不同相對風速及攻角下、動推力參數 值的影響。由升力曲線斜率及阻力極線方程式的分析得知，後推式螺旋槳動推力的USB效果優於前拉式推進型。半環形翼的空氣動力特性優於環形翼的空氣動力特性，且半環形翼及環形翼兩者的零攻角阻力係數值CD0、隨 值近乎成線性關係而增減。

This thesis is to study how to use CCW (Circulation Control Wing) concept in developing a Small Ring Winged Aerial Vehicle through aerodynamic testing in a wind tunnel. With a puller propeller on the top of the wing to control the circulation flow speed,it is also expected to gain more lift, through the Upper Surface Blowing (USB) concept. The wind tunnel testing of three models with the same airfoil section MH78, such as Rectangular Wing, Semicircular Channel Wing (CW) and Ring Wing (RW) have been done at some low Reynolds numbers (Re) and at low aspect ratio (AR=1) to examine the circulation control effects by using upper surface blowing. Both the lift-curve slopes and drag polar equations were obtained from the experiments at various angles of attack for each model. The effect of dynamic thrust factor is also examined for RW and CW models. The USB effect of wind tunnel testing results show that the pusher type is better than the puller type. The aerodynamic characteristics of the models show that the channel wing model is better than the ring wing model. and their CD0 is almost linear with respect to CT.

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