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以Spalart-Allmaras(S-A)湍流模型为计算模型,对风力机叶片NACA0018翼型在副翼摆角分别为0°、5°、10°和15°下的流体流动情况进行数值模拟,分析不同攻角下带副翼翼型上升阻力性能曲线以及翼型表面压力分布云图和流场流线图,研究不同摆角对带副翼翼型的空气动力学性能的影响。结果表明:相同攻角时,翼型的升力系数随着副翼摆角的增大而减小;副翼摆角的增大可以增大翼型的失速攻角,改善翼型周围流体的流动状况,提高翼型周围特别是副翼周围流体流动稳定性,抑制流动分离涡的形成。
Based on the Spalart-Allmaras (SA) turbulence model, the numerical simulation of the fluid flow of the NACA0018 airfoil at 0 °, 5 °, 10 ° and 15 ° angles of the ailerons was carried out. Angle rise with ailerons airfoil rise resistance performance curve and airfoil surface pressure distribution and flow field flow charts to study the different swing angle with aileron airfoil aerodynamic performance. The results show that the lift coefficient of airfoil decreases with the increase of ailerons at the same angle of attack, and the increase of ailerons’ angle can increase the angle of attack of airfoil stall and improve the fluid flow around the airfoils Condition, improve the fluid flow stability around the airfoil, especially around the ailerons, and suppress the formation of the flow separation vortex.