结冰区流场特征一致的混合缩比翼型设计

提出了一种基于翼型前缘范围流场相似的多控制点混合缩比翼型优化设计方法:以前缘局部范围内的空间流场特征相同为目标,采用多目标遗传优化算法结合翼型参数化、多控制点、网格自适应技术及CFD,进行了不同工况下的混合缩比翼型设计,分别通过低湍流度风洞及结冰风洞对翼型的气动性能及积冰过程进行了实验。设计及实验结果表明:该混合缩比翼型与对应的全尺寸翼型在前缘15%弦长范围内的压力系数偏差均在5%以内,翼型绕流相似;在相同时间历程内两者的冰型增长及气动特性均具有相同的变化规律。该设计方法可以应用于不同实验状态下的混合缩比翼型的设计,提高多状态下结冰实验效率。

Design of hybrid scale airfoil based on flow field characteristics of icing region

A multi-control point hybrid scale airfoil optimization method based on the similarity flow field in the leading edge was proposed.Multi-objective genetic optimization algorithm was used to design the hybrid scale airfoil under different conditions by taking the same spatial flow field characteristics in the leading edge as the objective by combining the airfoil parameterization, multiple control points, grid adaption and CFD.The aerodynamic performance and icing process of the airfoils were tested in the low turbulence wind tunnel and icing wind tunnel. The design and test results showed that the pressure coefficient deviation between hybrid scale airfoil and the corresponding full-scale airfoil in the 15% chord length range of the leading edge was within 5%, and the flow around the airfoil was similar.The ice accretion and aerodynamic characteristics of the two airfoils had similar changing law. This method can be applied to design hybrid scale airfoil under different conditions, and improve the efficiency of multiple icing test states.