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

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.