凹凸前缘叶片气动性能与绕流流场数值研究

以NACA0018翼型为原始模型进行前缘结构设计,采用计算流体动力学(CFD)方法分析凹凸前缘结构参数对叶片绕流流动及气动性能的影响。结果表明:在0°～10°攻角范围内,凹凸前缘叶片气动性能与原始叶片基本一致,但在15°～25°攻角范围内,正弦波形凹凸前缘叶片升力系数最大提升20.2%;叠加波形凹凸前缘叶片在15°～25°攻角内,气动性能均有不同程度的下降,波峰处推迟分离,而在波谷分离提前,在吸力面每个波谷顺流方向叶片及展向形成反向涡对,相互卷吸并与主流掺混增加能量交换向尾缘处移动,改变了叶片原始流场反馈回路,阻碍了叶片展向涡及流向涡的发展。

Numerical Study on Aerodynamic Characteristics and Flow Fields of Airfoil with Wavy Leading Edge

with NACA0018 airfoil as the original model,the influence of the structural parameters of the wavy leading edge on the flow and aerodynamic performance of the leaves is analyzed with CFD (Computational Fluid Dynamics) method.The results show that the aerodynamic performance of the wavy front airfoil is essentially the same as that of the original airfoil with the angle of attack in the range of 0°~10°.With the angle of attack within the range of 15°~25°,however,the coefficient of lift of the sinusoidal wavy leading edge airfoil increases by a maximum of 20.2%,while the superimposed waveforms of the leading and trailing vanes have a decrease in aerodynamic performance.It is found that the separation is postponed at the peak,and the wave separation is advanced.The opposite vortex pair is formed in the direction of the downstream direction of each wave trough of the suction surface,and they are rolled and mixed with the main flow,increasing the energy exchange to the trailing edge.The feedback loop of the original flow field of the airfoil hinders the development of the spanwise vortex and the flow vortex.