开展结冰风洞过冷大水滴结冰试验验证了现有混合翼设计准则。结冰风洞过冷大水滴结冰试验条件采用大、小水滴两种喷嘴组合喷雾实现了与冻毛毛雨水滴质量“双峰”分布曲线非常符合的过冷大水滴结冰环境模拟。以0.50 m弦长的NACA0012翼型为原始翼型，基于面向工程、面向适航的混合翼设计准则通过求解Navier-Stokes（NS）方程计算翼面压力分布，以混合翼与原始翼型驻点位置和前缘吸力峰值尽可能重合为目标，在保证前缘附近与原始翼型相同的基础上混合翼的设计弦长缩短50%。在结冰风洞中开展冻毛毛雨环境下的结冰试验验证混合翼设计效果，结果显示混合翼型与原始翼型模型前缘表面的冰形特征基本一致，局部冰形存在少量差异，混合翼型模型表面冰形冰高略偏大。所得结论表明现有混合翼设计准则在冻毛毛雨环境下依旧适用，可供后续开展相关民机型号的过冷大水滴结冰风洞试验参考。

An icing wind tunnel supercooled large droplet icing test was carried out to verify the design criteria of a hybrid wing. The test conditions adopt the combination of large and small water drop nozzles to achieve the “double peak” distribution characteristic. The NACA0012 airfoil with a chord length of 0.50 m is used as the original airfoil， and the hybrid wing design criteria for engineering and airworthiness are employed to design the hybrid wing. The Navier-Stokes （NS） equation is used to calculate the airfoil pressure distribution with the goal of overlapping the stagnation point position of the hybrid wing with the original airfoil and the suction peak at the leading edge as much as possible. The designed chord length of the hybrid wing was shortened by 50%. The design effect of the hybrid wing was verified by the icing wind tunnel supercooled large droplet icing test. The ice shape characteristics of the original airfoil and the hybrid airfoil model are basically the same， and the ice height of the hybrid airfoil model is slightly higher. It was verified that the design criteria of the hybrid wing are still suitable for the icing wind tunnel supercooled large droplet icing test， providing technical support for the follow-up of the supercooled large droplet icing wind tunnel test of related civil aircraft models.