本研究旨在探討微泡致動器應用於減低不同細長比彈體在高攻角產生之側向力；風洞模型為一個錐形彈體，其細長比之變化可由4.4至8，在圓錐表面則貼有陣列式微泡致動器；實驗是利用量力計、壓力感測器及熱線探針量測彈體的側向力、表面壓力分佈及流場特性。

　　實驗結果顯示，當微泡致動器沒有致動時，彈體的截面側向力沿著軸向的分佈受到彈體兩側渦流的消長而呈現振盪的變化，振盪的幅度隨著攻角增加而增大，振盪的週期則隨著攻角增加而減小。當微泡致動器在弱渦流側適當位置致動時，對於不同攻角、旋轉角及細長比的彈體皆可有效減輕其高攻角之側向力，表面壓力及流場量測結果指出微泡致動器致動時有效減輕彈體側向力之物理機制，其原因為致動器啟動後誘發的剪力層使得弱渦流側的第三渦流提早產生且強度增強，截面側向力的反向點因此往前移動因而大幅減輕彈體之側向力。

　　The study investigates that the side force reduction of the different slenderness body at high angle-of-attack using micro balloon array actuator. The wind tunnel model is a cone-cylinder slender body, whose slenderness can be changed from 4.4 to 8.0. The micro balloon array actuator can be packaged on curve surfaces of the cone. Side force, surface pressure and velocity are measured by using load cell, pressure transducer, and hot-wire anemometer.

　　The results show that the sectional side force of cone-cylinder exhibits an oscillatory behavior along the slender body for the control-free case. The oscillatory amplitude increases and the period decreases with higher angle-of-attack. When the actuator is actuated at the proper locations on the weak vortex side, the side force at high angle-of-attack can be effectively alleviated with the different angles-of-attack, roll angles, and slenderness. The results of surface pressure and velocity field indicate the cause of the side force reduction using micro balloon actuator. The main reason is that the shear layer near the micro balloon actuator induce third vortex to grow early. The zero crossing point of the sectional side force coefficient moves forward along the cylinder, and thus side forces at high angle-of-attack are alleviated.

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