中文摘要：

目前风力机翼型廓线都是基于单点攻角而设计出来，以追求局部极大气动特性，而忽略了一定多点攻角范围内的整体气动性能的提高。本文结合翼型B样条函数及复杂型线表面曲率光滑连续性思想，提出多点攻角情况下风力机翼型廓线设计方法，以解决翼型优化设计中气动力难以收敛这一问题，并实现翼型整体气动性能的提高。将多点攻角情况下设计出来的WQ？D翼型与单点攻角情况下设计出来的WQ？A翼型进行了气动性能对比分析。研究表明：相比WQ？A翼型，WQ？D新翼型系列整体气动性能均有显著提高，且表面曲率光滑连续性也更平滑，有利于翼型气动力收敛。该研究不仅验证了该设计方法的可行性，而且也表明WQ？D翼型通用性更广。

英文摘要：

The current airfoil design methods are based on a single-point angle of attack to determine the local maximum aerodynamic performance without considering the whole high aerodynamic performance within a multipoint angle of attack. This study presents a novel airfoil design method considering the multipoint angle of attack based on the airfoil B-spline function and complicated profile curvature smooth continuity theory. The method can make the aerodynamic force convergent and increase the whole aerodynamic performance. An aerodynamic comparison is made between the WQ-D airfoil series designed considering the multipoint angle of attack and the WQ-A airfoil series designed considering the single-point angle of attack. The results show that the WQ-D airfoil series exhibit a better overall performance than the WQ-A airfoil. Moreover, the WQ-D airfoil exhibits a smoother continuity, which benefits from the aerodynamic force convergence. This study verifies the feasibility of the novel design method and shows that the WQ-D airfoil series has a broad generality.