Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators
Separation Control on HIgh Angle of Attack Airfoil Using Plasma Actuators
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DOI：
10.2514/1.2929
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发表时间：
2004-11
期刊：
影响因子：
2.5
通讯作者：
M. Post;T. Corke
中科院分区：
文献类型：
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作者：
M. Post;T. Corke
这项工作涉及到在大迎角、远高于失速时翼型上发生的前缘流动分离的记录和控制。采用了一种通用翼型（NACA 663-018），因为它的前缘失速特性已被证明。它是用来测量表面压力的仪器，用于计算升力系数。翼型下游的平均速度剖面用于确定阻力系数。除此之外，还采用了烟流条纹显示来记录流动分离的状态。翼型在自由飞行速度为10 ~ 30 m/s，弦长雷诺数为77 × 103 ~ 333 × 103的范围内工作。第一个产生了一个展向排列的流向涡。第二个产生了二维射流的流动方向沿着表面的翼型。发现等离子体作动器在超过失速角8 °（研究的最高值）的攻角下导致再附着。这是伴随着一个完整的压力恢复和高达400%的升阻比增加。
This work involves the documentation and control of leading-edge flow separation that occurs over an airfoil at high angles of attack, well above stall. A generic airfoil shape (NACA 663-018) was used because of its documented leading-edge stall characteristics. It was instrumented for surface-pressure measurements that were used to calculate lift coefficients. Mean-velocity profiles downstream of the airfoil were used to determine the drag coefficient. In addition to these, smoke streakline flow visualization was used to document the state of flow separation. The airfoil was operated over a range of freestream speeds from 10 to 30 m/s, giving chord Reynolds numbers from 77 × 10 3 to 333 × 10 3 .T wo types of plasma actuator designs were investigated. The first produced a spanwise array of streamwise vortices. The second produced a two-dimensional jet in the flow direction along the surface of the airfoil. The plasma actuators were found to lead to reattachment for angles of attack that were 8 deg past the stall angle (the highest investigated). This was accompanied by a full pressure recovery and up to a 400% increase in the lift-to-drag ratio.