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本文根据翼型表面压力分布对边界层的影响,分析翼型表面压力分布的特点,以XFOIL计算软件为设计平台,采用其中的混合反设计模块,通过合理改变翼型表面的速度分布来得到气动特性满意的翼型。所设计的翼型主要要求具有高的设计升力系数、高的最大升阻比、良好的前缘粗糙不敏感性及和缓的失速特性。在提高设计升力系数的同时限制最大升力系数,以减小两者的差值,减小叶片的极限载荷。经计算分析,采用反设计优化得到的翼型与DU翼型相比具有很好气动特性。
According to the influence of airfoil surface pressure distribution on the boundary layer, the characteristics of airfoil surface pressure distribution are analyzed. XFOIL calculation software is used as the design platform. The mixed anti-design module is used to obtain the aerodynamic Characterized airfoil. The designed airfoil mainly requires high design lift coefficient, high maximum lift-drag ratio, good frontal roughness insensitivity and gentle stalling characteristics. In raising the design lift coefficient at the same time limit the maximum lift coefficient, in order to reduce the difference between the two to reduce the blade’s ultimate load. After calculation and analysis, the airfoil optimized by inverse design has good aerodynamic characteristics compared with DU airfoil.