多段翼构型结冰计算方法及结冰影响分析

Numerical simulation and aerodynamic performance effects of multi-element airfoil ice accretion

为了揭示不同来流条件下多段翼构型表面结冰特性,针对30P30N增升构型开展了结冰数值模拟研究。在计算方法方面,通过引入最小壁面距离,实现了基于拉格朗日方法的高效液滴收集率计算。采用局部网格拓扑重构技术改善了复杂冰形下网格重构稳健性差的问题,实现了更加鲁棒的多时间步结冰过程自动化计算能力。基于上述算法,开展了结冰特性及带冰后气动特性模拟,计算结果显示,多段翼结冰区域主要分布在前缘缝翼迎风面、主翼段及襟翼下翼面。在上游部件尾迹的影响下,多段翼表面水滴收集特性呈现显著的动态分布特性。前缘缝翼表面形成的冰角结构及其缝道附近发生的积冰堵塞是导致多段翼构型气动性能退化的主要因素,相比之下襟翼表面结冰对气动特性的影响程度较小。

Icing simulation of a 30P30N multi-element airfoil is conducted to explore the aerodynamic characteristics influenced by ice shape on the multi-element airfoil under different inflow conditions.An improved multi-time step calculation method based on the Myers icing phase transition model is proposed.A robust and efficient Lagrangian water collection calculation is realized by introducing the minimum wall distance.The local mesh repair technique is applied to improve the robustness of mesh reconstruction under complex ice conditions.The calculation results show that the ice shape is distributed at the leading edge of the slat airfoil and the lower surface of the main element and the flap airfoil.The droplet collection on the multi-element airfoil surface has significant unsteady characteristics due to the influence of the upstream component wake.Ice accretion on the leading edge slat and ice blocking in the crack near the slat are the main factors leading to the aerodynamic performance degradation,while the ice on the flap surface has a smaller impact for the lift and drag efficiency.