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EXPERIMENTAL FLOW VISUALIZATION STUDY OF FLOW SEPARATION CONTROL WITH HIGH-FREQUENCY TRANSLATIONAL SURFACE ACTUATION

机译:高频平移表面致动流动分离控制的实验流程可视化研究

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Flow separation causes aircraft to experience an increase in drag degrading their aviation performance. The current study aims to delay flow separation on an airfoil by embedding a high-frequency translational piezoelectric actuator along the surface of the airfoil. The actuators with two actuation surfaces were embedded on the suction surface of an Eppler 862 airfoil model and placed in a low-speed wind tunnel. Consecutive pictures of the flow fields with dry ice fogs around the airfoil were taken using a high speed camera in order to observe the flow separation phenomenon before and after turning on the high-frequency translational surface actuation. The effects of the actuation on the flow separation were observed at various actuation displacements, angles of attack, and free stream velocities. The operating frequency of the surface actuation was 565 Hz. The measured actuation mean-to-peak displacement ranged up to 0.12 mm at the maximum applied voltage of 150 V. The angle of attack of the airfoil varied from 6° to 24°. The chord Reynolds number was increased up to around 262,000. It was confirmed that the actuation had a very strong influence on the flow separation even at a very small displacement of 0.024 mm remaining significantly reduced separation bubble compared to the one before activating the actuators at 4.3 m/s of velocity and 14° of angle of attack. The flow separation was completely suppressed when the actuation displacement reached around 0.082 mm under the same conditions of flow velocity and angle of attack. This implied that the actuation should generate a strong enough momentum relative to the free stream in order to completely suppress the flow separation. In summary, the study confirmed that the employed high-frequency translational surface actuation had the obvious control authority on delaying or suppressing the flow separation over the airfoil depending on the parameters changed.
机译:流动分离导致飞机体验拖动的增加,降低其航空性能。目前的研究旨在通过沿着翼型的表面嵌入高频平移压电致动器来延迟翼型的流动分离。具有两个致动表面的致动器嵌入到Eppl 862翼型模型的吸入表面上并放置在低速风洞中。使用高速相机拍摄翼型周围的围绕翼型的干冰雾的流场的连续照片,以观察在接通高频平移表面致动之前和之后的流动分离现象。在各种致动位移,攻击和自由流速度观察到致动对流动分离的影响。表面致动的工作频率为565Hz。测量的致动平均峰位位移在150 V的最大施加电压下高达0.12毫米。翼型的迎角从6°变化到24°。和弦雷诺数数量增加到约262,000。已经证实,即使在将致动器的速度和14°的角度为4.3米/秒和14°的角度下,致动使在0.024mm的非常小的位移显着减小的分离气泡的情况下,致动即使在0.024mm的非常小的位移的情况下也具有非常强烈的影响。攻击。当致动位移在相同的流速和攻角条件下致动位移达到约0.082mm时,完全抑制了流动分离。这意味着致动应该产生相对于自由流的足够强的动力,以便完全抑制流动分离。总之,该研究证实,采用的高频平移表面致动具有明显的控制权,根据参数改变的参数延迟或抑制翼型上的流动分离。

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