传统容冰气动力优化设计方法难以完全兼顾常规飞行和结冰状态对翼型几何特征的矛盾需求。依据前缘下垂变弯度的思路创新性地提出了一种能有效协调和解耦翼型气动/容冰特性的解决方案。针对GLC305-944结冰翼型典型过失速状态开展了基于IDDES（Improved Delayed Detached Eddy Simulation）方法的前缘下垂前后容冰特性对比分析，表明前缘下垂后结冰翼型失速特性显著改善，前缘吸力以压力平台形式恢复，分离泡形态由大尺度全局回流退化到冰角后方的局部流动结构，湍流脉动影响范围约束于前缘近壁面有限区域内。由于前缘下垂后冰角与当地壁面组成类凹腔结构，剪切层涡系经短暂发展后能迅速在壁面附近触发掺混融合-动量输运效应，有效促进再附过程，导致时均再附点提前、混合层厚度降低、分离泡几何尺度减缩，这是容冰特性改善的主要机制。

Traditional aerodynamic optimization method of ice-tolerance encounters difficulties in completely taking into account the contradictory requirements of the conventional flight and icing state for airfoil geometric characteristics. Based on the idea of the variable camber in drooping the leading edge， we propose a new solution to the coordination and decoupling of the aerodynamic and ice-tolerance performance of airfoils. The numerical simulation of post-stall separation of the GLC305-944 iced airfoil before and after drooping the leading edge is conducted with the Improved Delayed Detached Eddy Simulation （IDDES） method. The results show that the stall performance of the iced airfoil is significantly improved after drooping the leading edge， and the suction of the leading edge is recovered in the form of pressure plateau. The structure of the separation bubble is degraded from a global large-scale recirculation region to a local flow structure after the horn while the influence of turbulence fluctuation is controlled in the limited region near the leading edge. Since the horn ice and the local wall form a special cavity structure after the leading edge drooping， both the mixing effect and the momentum transport will be directly induced near the wall after a short development process of the shear-layer vortices， thus the reattachment is effectively promoted. Therefore， the time-average reattachment point is shifted forward and the thickness of the mixing layer is reduced， forming a separation bubble structure with a limited scale. This is the basic mechanism for the improvement of ice-tolerance capacity.