臺灣博碩士論文加值系統

　　電漿致動器主要作用原理是在飛行體表面通以高壓電場解離鄰近氣體形成電漿，藉由電場誘導產生的離子風(Ionic wind)來改變邊界層速度分佈。因應不同載體和需求，改變其空氣動力特性，例如延遲氣流分離(Delay flow separation)、降低壓力阻力(Pressure drag)等。電漿致動器根據其構造不同可大略分為兩大類：光暈放電(Corona discharge)以及介電質放電(Dielectric barrier discharge) 。
　　本研究採用介電質放電，探討比較三角翼在不同位置擺設致動器，於低雷諾數及不同攻角時的空氣動力特性；研究中使用兩片銅箔作為電極，聚醯亞胺薄膜(Kapton film)作為介電質，並使用玻璃皮托管來測量誘導產生的離子風在不同位置的速度分佈。實驗在低速風洞中進行，以力平衡儀進行氣動力量測，同時藉視流觀察三角翼左右兩側渦流大小的改變；實驗結果發現，電漿致動器有效地改變翼?渦流(Leading edge vortex)的結構，致動器擺放位置另一側的渦流潰散(Vortex breakdown)現象明顯延後，因而造成升力及翻轉力矩係數的有效提升。另外，致動器放置在三角翼前段能夠較有效提升升力及翻轉力矩係數，在雷諾數75,000以及高攻角的狀態之下，致動器的影響效果會比較高雷諾數(Re=100,000、125,000)和低攻角的情況來得明顯。

　　The working principle of plasma actuators is to apply a high voltage electric field to ionize the air around the surface of electrodes attached to an aerial vehicle. Ions produced at the electrode drift from the injection electrode to the collecting one under the effect of electric field. These ions exchange momentum with the neutral fluid particles and induce fluid movement, so called electric ionic wind. Its objective is to accelerate the airflow tangentially and very close to the wall, in order to modify the airflow profile inside the boundary layer and change the aerodynamic characteristics of the aerial vehicle, for example, delaying the flow separation, reducing the vehicle drag…etc. Plasma actuators can be categorized as corona discharge and dielectric barrier discharge (DBD) types.
　　This research focuses on the application of the dielectric barrier discharge actuators on a delta wing. The effects of the DBD actuators on the aerodynamics of a delta wing at different angles of attack and Reynolds numbers are investigated. The actuator is composed of two copper strips separated by a dielectric Kapton film. The ionic wind velocity profiles at different positions from the delta wing edge are measured by a glass pitot tube. The experiments are conducted in a low speed wind tunnel. The force balance is used to measure the aerodynamic force, and the smoke wire technique is adopted to visualize the leading edge vortices of the delta wing. The results show that the plasma actuator when put on one side has a significant effect on the leading edge vortex structure of the other side and delays its breakdown, which enhance the lift and roll moment accordingly. The actuators are more effective in the fore positions than in the aft ones. Finally, the actuators show the largest increases in the lift and roll moment coefficients at Reynolds number 75,000 and high angles of attack near stall.

中文摘要 I
ABSTRACT III
誌謝 V
目錄 VII
表目錄 X
圖目錄 XI
符號表 XIV
第一章　序論 1
§1.1 前言 1
§1.2 電漿致動器原理 3
§1.3 文獻回顧 6
§1.3.1 電流體動力學致動器（Electrohydrodynamic actuator） 6
§1.3.2 基本幾何模型之研究 12
§1.3.3 其他方面之應用 14
§1.3.4 數值模擬 15
§1.3.5 無因次參數 19
§1.3.6 三角翼文獻回顧 20
§1.4 研究動機與目的 21
第二章　實驗方法與設備 22
§2.1 水洞 23
§2.2 低速風? 23
§2.2.1 皮托管及壓力轉換器 24
§2.2.2 外置式應變規力平衡儀 25
§2.2.3 A/D轉換器 25
§2.3 玻璃皮托管 25
§2.4 三角翼模型 27
§2.5 電漿致動器之製作 28
§2.5.1 高壓電設備 28
§2.5.2 致動器結構 29
§2.5.3 高壓衰減探棒(High voltage probe) 30
§2.6 實驗步驟 31
§2.7 翻轉係數(Roll moment coefficient)之計算 32
第三章　結果與討論 35
§3.1 三角翼染液視流實驗結果 35
§3.2 電漿致動器實驗結果 37
§3.3 電漿致動器附近的速度分布 39
§3.4 氣動力量測結果 41
§3.5 煙線視流結果 50
第四章　結論與建議 59
§4.1 結論 59
§4.2 建議 60
參考文獻 61

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