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首页> 外文期刊>Journal of Fluid Science and Technology >An Attempt for Suppression of Wing-Tip Vortex Using Plasma Actuators
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An Attempt for Suppression of Wing-Tip Vortex Using Plasma Actuators

机译：用等离子作动器抑制翼尖涡流的尝试

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Influence of the flow induced by dielectric barrier discharge (DBD) plasma actuators on the wing-tip vortex is investigated numerically and experimentally. The plasma actuators are installed on the suction side of the NACA0012 airfoil and operated in blowing and suction modes. For the numerical simulation, direct numerical simulation (DNS) based on the finite-difference immersed-boundary method is used. The DNS shows that the circulation parameter, which measures the strength of wing-tip vortex, is reduced by blowing as well as suction. At the same time, however, the lift-to-drag ratio is found to decrease by the actuation. In the experiment, a wing model with plasma actuators is set inside the wind tunnel and the velocity fields are measured using a PIV system. Although suppression of wing-tip vortex is not confirmed due to insufficient strength of actuation and insufficient length of measurement area, the change of streamwise mean velocity profile is found to be similar to that of DNS.
机译：数值和实验研究了由介质阻挡放电（DBD）等离子体致动器引起的流动对翼尖涡旋的影响。等离子致动器安装在NACA0012机翼的吸气侧，并以吹气和吸气模式运行。对于数值模拟，使用基于有限差分沉浸边界方法的直接数值模拟（DNS）。 DNS显示，通过吹气和吸力会降低测量翼尖涡旋强度的循环参数。然而，与此同时，发现升降比由于致动而减小。在实验中，在风洞内部设置了带有等离子体致动器的机翼模型，并使用PIV系统测量了速度场。尽管由于致动强度不足和测量区域长度不足而未确认抑制翼尖涡旋，但发现沿流平均速度剖面的变化与DNS相似。

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