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应用CFD软件,对几种典型覆冰形态的流场进行研究。分析结果表明:前缘覆冰改变了翼型的气动外形,使流动更易出现分离现象,造成升力减小,阻力增大,零升迎角i0增大。沿弦向生长的覆冰保持流线型的截面形状,对边界层流动影响相对较小;向上翼面或下翼面生长的覆冰可使该翼面边界层流动分离,造成翼型气动性能的下降。随着前缘覆冰长度的增加,覆冰可导致翼型的升力增加、失速滞后,这种现象类似于前缘襟翼效应。
CFD software was used to study the flow field of several typical icing patterns. The results show that the ice coating changes the aerodynamic shape of the airfoil, making the flow easier to separate, resulting in less lift, more resistance, and greater i0. The icicles growing in the chordal direction keep a streamlined cross-sectional shape, which has a relatively small influence on the boundary layer flow. Ice covering the upper or lower airfoil can separate and flow the airfoil boundary layer, resulting in a decrease in the aerodynamic performance of the airfoil . With the increase of the length of the front icing, icing can lead to the increase of the lift of the airfoil and the lag of the stall, which is similar to the leading edge flap effect.