本研究將利用風洞實驗之方法觀察電漿致動器作用於三角翼翼前緣空氣動力特性之變化。其空氣動力特性的不同，為透過控制電漿致動器的高壓電場可將致動器周圍的空氣解離，同時所誘導出的離子風進而改變邊界層的速度分布。
本研究三角翼於風洞內所量測的角度可分為正對流場與側滑角二項。首先在側滑角為-5˚、-2.5˚、+2.5˚與+5˚時利用力平衡儀於雷諾數70000、115000與140000量測三角翼之側向力係數、滾轉力矩係數與偏轉力矩係數。最後再開啟電漿致動器，探討三角翼大於失速攻角後流場穩定之現象。
結果顯示穩態電漿致動器開啟後在低雷諾數的情況下，對於三角翼之滾轉力矩以及三角翼穩定度皆有一定之影響力，並且，當實驗加入側滑角之條件後，結果亦然。

The aim of this study is to investigate the aerodynamic performance of a delta wing using the airflow control method. The wind tunnel experiment is used to obtain the aerodynamic characteristics as a surface plasma actuator, set on the leading edge of a delta wing. Dielectric barrier dischargers are used to ionize locally the air and to produce the ionic wind that will modify the velocity profiles in the boundary layer.
The experiments were divided into three parts. First, the aerodynamic performance is measured at the sideslip angle of 0° and the second is obtained in the sideslip angles of -5˚, -2.5˚, +2.5˚ and +5˚. Finally, the investigation into the stability of delta wing was carried out while turn on the plasma actuator. All cases in the wind tunnel experiment were performed at the low Reynolds numbers of 7×104 to 1.4×105 to obtain the values of non-dimensional parameters such as side force coefficient, roll moment coefficient, and yaw moment coefficient.
These results indicated that the proposed steady mode dielectric barrier discharge plasma actuators can effectively control the Delta wing in the roll motion and stability even with sideslip angles along the freestream in low Reynolds number.

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