The size of aircraft models that can be tested in icing wind tunnels is limited by the dimensions of the facilities in present; it is an effective method to replace the large model with a hybrid airfoil to carry out the experiment. A design method of multiple control points for hybrid airfoil based on the similarity of flow field in the leading edge of airfoil is proposed. Aiming at generating the full-scale flow field and ice accretion on the leading edge, multiobjective genetic optimization algorithm is used to design the hybrid airfoil under different conditions by combining the airfoil parameterization and solution of spatial constraint. Pressure tests of hybrid airfoils are carried out and compared with the leading edge pressure of the corresponding full-scale airfoils. The design and experimental results show that the pressure coefficient deviation between the hybrid airfoils designed and the corresponding full-scale airfoil in the 15% chord length range of the leading edge is within 4%. Finally, the vortex distribution and ice accretion process of the two airfoils were simulated by the unsteady Reynolds-averaged-Navier–Stokes (URANS) equations and multistep ice numerical method; it is shown that the hybrid airfoil can provide the same vortex distribution and ice accretion with the full-scale airfoil.

中文翻译：

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混合翼型在风洞结冰试验中的参数化设计方法

可以在结冰风洞中进行测试的飞机模型的大小受到目前设施规模的限制；这是用混合翼型代替大型模型进行实验的有效方法。提出了一种基于翼型前缘流场相似性的混合翼型多控制点设计方法。为了在前沿产生全尺寸流场和积冰，采用多目标遗传优化算法，结合翼型参数化和空间约束解，设计了不同条件下的混合翼型。进行混合翼型的压力测试，并将其与相应的满量程翼型的前沿压力进行比较。设计和实验结果表明，在前缘的弦长15％范围内，设计的混合翼型与相应的满量程翼型之间的压力系数偏差在4％以内。最后，通过非定常的雷诺平均Navier-Stokes（URANS）方程和多步冰数值方法模拟了两个翼型的涡旋分布和积冰过程。结果表明，混合翼型可以提供与全尺寸翼型相同的涡流分布和积冰。用非稳态雷诺平均纳维-斯托克斯方程（URANS）和多步冰数值方法模拟了两个翼型的涡旋分布和积冰过程。结果表明，混合翼型可以提供与全尺寸翼型相同的涡流分布和积冰。用非稳态雷诺平均纳维-斯托克斯方程（URANS）和多步冰数值方法模拟了两个翼型的涡旋分布和积冰过程。结果表明，混合翼型可以提供与全尺寸翼型相同的涡流分布和积冰。