翼涡干扰前缘开孔被动控制数值研究

开孔方法是一种简单的流动被动控制方法.为找到一种有效降低桨涡干扰效应的被动控制方法，以NACA 0012翼型作为研究对象，建立了4种前缘开孔的模型.在不同来流速度、涡的强度和干扰距离条件下，对4种前缘开孔模型和无孔的基准翼型进行了二维平行桨涡干扰（翼涡干扰）数值模拟，对比了升力系数的变化.结果表明:前缘开孔可以降低翼涡干扰效应，但对翼型升力系数有一定的影响；宽度为2.5%弦长的直孔能在翼型升力系数损失较小的情况下有效地降低翼涡干扰效应，且适用范围较广.

Numerical Study on Passive Control of Airfoil-Vortex Interaction Based on Slotted Leading Edges

The slotting method is a simple flow passive control method. In order to search for a passive control method that can effectively mitigate the blade vortex interaction effects, a NACA 0012 airfoil was used as the research object, 4 kinds of the NACA 0012 airfoil models with differently slotted leading edges were designed. Numerical simulations of 2D parallel blade vortex interaction (airfoil vortex interaction) were performed for the slotted airfoils and the benchmark airfoil to examine the effects of the freestream velocity, the vortex strength and the disturbing distance on the lift coefficient. The results show that, the slotted leading edge can mitigate the airfoil vortex interaction effects, but with an influence on the lift coefficient. The vertical cavity with a width of 2.5% of the chord length can obviously mitigate the airfoil vortex interaction effects with low lift coefficient penalties, having a wide application range.