Single Dielectric Barrier Discharge Plasma Actuators for Improved Airfoil Performance
Single Dielectric Barrier Discharge Plasma Actuators for Improved Airfoil Performance
复制标题
单介质阻挡放电等离子体致动器可提高翼型性能
DOI：
10.2514/1.37638
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发表时间：
2009
影响因子：
2.2
通讯作者：
I. Wygnanski
中科院分区：
文献类型：
--
作者：
J. Mabe;F. Calkins;Benjamin Wesley;R. Woszidlo;L. Taubert;I. Wygnanski
在本研究中，评估了单辩证阻挡放电等离子体作动器作为主动流动控制装置的适用性，该装置能够提高翼型的性能。测量进行了两个厚翼型与简单的襟翼：一个NACA0021和一个翼型，是类似于那些通常用于倾转旋翼飞机。翼型的弦长分别约为0.3和0.25 m，跨度约为0.6 m。它们都在同一风洞中进行了测试，测试截面为0.6 x 1.1 m。测试的自由流速度为5 ~ 15m /s，对应的弦雷诺数为0.8 × 10.5 ~ 3 × 10.5。升力、力矩和形式阻力从翼型表面的压力分布中获得，总阻力从尾迹调查中计算出来。测试了入射角α在- 4°<α < +20°的范围内，襟翼偏转δ f为0°和15°。驱动器的位置也被改变了。提出了两个数据集：其中一个执行器被放置在约5%的弦，而另一个执行器位于皮瓣肩的上游，在约75%的弦位置。用热丝测量了单辩证法阻挡放电等离子体致动器的动量输入，与先前发表的结果很好地一致。输入动量非常弱，不足以阻止雷诺数大于100,000的分离。本研究中使用的单辩证法屏障放电等离子体致动器可能仅在非常低的雷诺数下提供足够的动量才能有效，例如适用于微型飞行器的雷诺数。在特殊情况下，它们在表面的被动存在可能会干扰边界层，使其更难以分离，但在这种情况下，适当的粗糙度条或涡发生器可能更有效地延迟分离。
The applicability of single dialectic barrier discharge plasma actuators for use as active flow control devices, capable of enhancing the performance of airfoils, was assessed in this investigation. Measurements were carried out on two thick airfoils with simple flaps: a NACA0021 and an airfoil that is similar to those commonly used on tiltrotor aircraft. The chord length of the airfoils was approximately 0.3 and 0.25 m, respectively, and the span was approximately 0.6 m. They were both tested in the same wind tunnel with a test section of 0.6 x 1.1 m. Freestream velocities varying from 5 to 15 m/s were tested, corresponding to chord Reynolds numbers ranging between 0.8 × 10 5 and 3 × 10 5 . The lift, moment, and form drag were obtained from the pressure distributions over the airfoil's surface, and the total drag was calculated from a wake survey. The range of incidence angles α varied from ―4deg <α < +20 deg and flap deflections δ f of 0 and 15 deg were tested. The location of the actuation was also altered. Two data sets are presented: one in which the actuator was placed at approximately 5 % of the chord and the other in which it was located just upstream of the flap shoulder at a chord location corresponding to about 75 %. The momentum input of the single dialectic barrier discharge plasma actuators was measured with a hot wire and was in good agreement with previously published results. The input momentum is very weak and is not sufficient to prevent separation at Reynolds numbers greater than 100,000. The single dialectic barrier discharge plasma actuators used in this study may only provide sufficient momentum to be effective at very low Reynolds numbers, such as those appropriate to micro air vehicles. Under special circumstances, their passive presence on the surface may trip the boundary layer, making it more resistant to separation, but in those cases, a proper roughness strip or vortex generators may delay separation more effectively.