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采用斜出口合成射流对低雷诺数自由翼进行分离流主动流动控制,通过可视化机翼表面压力测试技术和粒子图像测速技术的同步测量,探究了合成射流对自由翼平衡迎角的提升效果及合成射流作用后自由翼迎角突跃的物理机制。实验结果表明:在低雷诺数来流条件下(Re=1.24×105),自由翼的最大平衡迎角仅为5°;合成射流控制下,最大平衡迎角增至16.8°。无控制状态下,当自由翼平衡迎角达到5°时,上翼面流动分离,处于分离区内的操纵舵面舵效降低。斜出口合成射流激励器在边界层内的能量注入,使自由翼上翼面分离流再附,提高了操纵舵效,促使自由翼迎角突跃,在较大的迎角下保持稳定。在斜出口合成射流激励器的作用下,自由翼可以配平在大迎角飞行状态,对于实现短距起降具有重要的意义。
By using the inclined jet synthesis jet to control the flow at low Reynolds number of free wings, the effect of synthetic jet on the free-wing equilibrium angle-of-attack and the synthesis of the free jet were studied through the simultaneous measurement of visualized wing surface pressure and particle image velocimetry The Physical Mechanism of Free Wing Anger Angle Jump after Jet Action. The experimental results show that the maximum equilibrium angle of attack of the free wing is only 5 ° under low Reynolds number flow (Re = 1.24 × 105), and the maximum angle of attack increases to 16.8 ° under the control of the synthetic jet. In the uncontrolled state, when the free wing’s equilibrium angle of attack reaches 5 °, the upper airfoil flows separate and the rudder helm effect in the separation zone decreases. The energy injection into the boundary layer by the oblique exit synthetic jet exciter can separate the flow on the free airfoil and improve the manipulative rudder effect and promote the sudden rise of the freewing angle of the free wing and maintain the stability at the larger angle of attack. Under the effect of the jet ejector, the free wing can be trimmed at high angle of attack, which is of great significance for short-range take-off and landing.