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针对所设计的三角形涡流发生器开展用于翼型失速流动控制的风洞实验研究,重点讨论涡流发生器几何参数、方向角、安装位置及实验雷诺数等因素对翼型失速流动控制的影响。实验结果表明:涡流发生器作用下,在干净翼失速迎角后能够形成一个升力几乎不随迎角变化的相对稳定的高升力状态,抑制了失速流动的发生,与此同时阻力大幅下降;本文所设计的涡流发生器方向角过大时会削弱翼型失速流动控制的效果;同一涡流发生器作用下雷诺数过大其失速流动控制效果会急剧恶化,第一种涡流发生器控制翼型失速的雷诺数有效范围略宽于第二种涡流发生器。
The wind tunnel experiment for the control of airfoil stall flow is carried out for the designed triangular vortex generator, and the influence of geometrical parameters of vortex generator, orientation angle, installation position and experimental Reynolds number on the control of airfoil stall flow is discussed. The experimental results show that under the action of a vortex generator, a relatively stable high-lift state where the lift hardly changes with the angle of attack can be formed after the stall angle of attack of the clean wing, and the occurrence of stalling flow is suppressed, meanwhile, the resistance greatly decreases. If the direction angle of the vortex generator is too large, the effect of airfoil stalling flow control will be impaired. If the Reynolds number is too large due to the same vortex generator, the effect of stalling flow control will be drastically deteriorated. The first vortex generator controls the stalling of the airfoil The effective range of Reynolds number slightly wider than the second vortex generator.