The icing on the aircraft induces a severe problem for the safety, and development of the simulation method has been required. In the present study, the effects of several icing conditions consisting of inflow velocity, liquid water content and angle of attack, on ice accretion on an airfoil are numerically investigated using a particle-based method. The computational target is NACA0012 airfoil with the chord length of 0.53 m and the droplets diameter is 1.0 mm for all cases. The icing simulations are carried out at different inflow velocity, liquid water content and angle of attack ranging from 50 ~ 140 m/s, 0.2 ~ 1.6 g/m3 and -8 ~ 20 degrees with the standard values of 50 m/s, 1.2 g/m3 and 4 degrees, respectively. The explicit moving particle simulation method, which is based on Lagrangian approach, is employed to obtain complex ice shapes such as horn and feather. Moreover, the aerodynamic performances before and after the icing are compared at different attack angles using ice shapes obtained from the moving particle method. It was confirmed that the feather shape, which is difficult to produce by the present lattice method, was reproduced using a particle-based method. Furthermore, the results indicated that the icing makes the stalling angle smaller and deteriorates the aerodynamic performance by 56.2 % at most.

中文翻译：

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使用E-MPS方法评估结冰后的空气动力性能

飞机上的结冰给安全性带来了严重的问题，因此需要开发仿真方法。在本研究中，使用基于粒子的方法，数值研究了几种结冰条件（包括进水速度，液态水含量和攻角）对机翼上积冰的影响。计算目标为NACA0012翼型，弦长为0.53 m，所有情况下的液滴直径均为1.0 mm。在不同的进水速度，液态水含量和迎角为50〜140 m / s，0.2〜1.6 g / m3和-8〜20度的情况下进行结冰模拟，标准值为50 m / s，1.2 g / m3和4度。基于拉格朗日方法的显式运动粒子模拟方法，用来获得复杂的冰形状，例如角和羽毛。此外，使用从运动粒子方法获得的冰形，比较了在不同结冰角度下结冰前后的空气动力性能。证实了使用基于粒子的方法再现了通过本发明的格子法难以制造的羽毛形状。此外，结果表明，结冰使失速角更小，并且空气动力学性能最多降低56.2％。