Icing on aircraft can drastically reduce aerodynamic performance and lead to serious accidents. Therefore, prediction of the accreted ice shape and area and its effects on aerodynamic performance is crucial during the design phase of an aircraft. However, numerical simulations based on conventional grid-based methods such as the finite volume method cannot accurately reproduce the complex ice shapes, which involve horn growth, feather growth, air voids, and severe surface roughness. In the present study, instead of the grid-based method, a hybrid grid- and particle-based method was newly proposed and applied to the icing problem on a NACA0012 airfoil. The explicit moving particle semi-implicit method was employed as the particle-based method due to its short computing time. The numerical simulations effectively reproduced feather-shaped ice, air voids, and surface roughness. Finally, by computing the flow around the iced airfoil, it was confirmed that flow separation around the leading edge occurred due to the ice layer, which resulted in a thicker boundary layer and wake and an increase in the drag coefficient of approximately 70% after a residence time of only 60 seconds.

在飞机上结冰会大大降低空气动力性能并导致严重事故。因此，在飞机的设计阶段，预测积冰的形状和面积及其对空气动力性能的影响至关重要。但是，基于传统的基于网格的方法（例如有限体积法）的数值模拟无法准确地再现复杂的冰形状，这些复杂的冰形状涉及角生长，羽毛生长，空气空隙和严重的表面粗糙度。在本研究中，代替基于网格的方法，新近提出了一种基于网格和粒子的混合方法，并将其应用于NACA0012机翼的结冰问题。由于显式运动粒子半隐式计算时间短，因此被用作基于粒子的方法。数值模拟有效地再现了羽毛状的冰，气孔和表面粗糙度。最后，通过计算冰翼周围的流动，可以确认由于冰层而导致了前缘周围的流动分离，这导致了较厚的边界层和尾流，并且在飞行后，阻力系数增加了约70％。停留时间只有60秒。