基于涡流发生器的翼型失速流动控制及雷诺数效应影响研究

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。

Investigation on Airfoil Stall Flow Controlling and Reynolds Number Effect Based on a Vortex Generator

Wind tunnel investigation was carried out to control the stall flow over airfoil by using vortex generator (VG), and the focus was on the discussion of the effect related to the vortex generator geometric parameters, such as inclined angle, and location as well as Reynolds number etc. Experimental results show that for a clean airfoil, behind the stall inclined angle, the lift keeps nearly as a constant without the variation with inclined angle, and the vortex generator can suppress flow separation. In the mean time, the drag after stall is markedly reduced. When the inclined angle of vortex generator is too large, the control effect of stall flow over airfoil is weakened. When Reynolds number is too large, the controlling effect of stall flow over airfoil with the same vortex generator sharply worsens. The effective Reynolds number range, in which vortex generator can suppress stall flow separation, is broader for No.1 VG than that of No.2 VG.