大型飞机全尺寸多段翼结冰特性计算和试验
收稿日期: 2024-11-27
修回日期: 2024-12-02
录用日期: 2024-12-24
网络出版日期: 2025-01-07
基金资助
国家自然科学基金重点基金(12132019)
Icing characteristics of full-scale multi-element configurations of large aircraft: Computation and experiment
Received date: 2024-11-27
Revised date: 2024-12-02
Accepted date: 2024-12-24
Online published: 2025-01-07
Supported by
The Key Program of National Natural Science Foundation of China(12132019)
采用数值模拟和大型结冰风洞试验相结合的方法，开展了典型大飞机全尺寸三段翼的结冰特性研究。基于结冰数值计算软件NNW-ICE发展了适合于多段翼结冰模拟的计算方法，包括液滴收集计算的高效拉格朗日算法，考虑液膜非定常流动特性的结冰相变计算方法，适合于多时间步结冰计算的结冰界面、网格重构方法。在此基础上，采用NNW-ICE进行了典型状态下三段翼结冰计算，并在中国空气动力研究与发展中心的3 m×2 m大型结冰风洞开展了该翼型的全尺寸试验，重点分析了缝翼背面的结冰特性。结果表明，除了缝翼、主翼的迎风面前缘，襟翼的下翼面有结冰，缝翼背面也会结冰。研究发现了缝翼背面冰形会表现出独特的双冰脊形态，并通过计算分析，揭示了双冰脊现象形成的原因，可为飞机增升装置、防除冰设计提供参考。
易贤 , 任靖豪 , 赖庆仁 , 刘宇 , 王强 . 大型飞机全尺寸多段翼结冰特性计算和试验[J]. 航空学报, 2025 , 46(5) : 531575 -531575 . DOI: 10.7527/S1000-6893.2024.31575
A study on ice accretion characteristics of the full-size tri-element airfoil of typical large airplane was conducted using a combined approach of numerical and experimental methods. Numerical techniques specifically developed for simulations of icing on multi-element airfoil structures were implemented on the NNW-ICE software platform. These techniques include a highly efficient Lagrangian method for droplet collection， an icing simulation method featuring the unsteady flow of water film， and a reconstruction method for calculating the evolution of volume grids and ice layers in multi-shot icing simulations. Then， the full-size tri-element airfoil was utilized in simulations using the NNW-ICE software， as well as in experimental tests conducted in the 3 m × 2 m large-scale icing wind tunnel at the Chinese Aerodynamics Research and Development Center. A detailed analysis was performed on the icing characteristics of the back of the slat wing. The results indicate that ice can unexpectedly accumulate on the lower side of the flap wing and the back of the slat wing， in addition to the accumulation observed on the windward leading edge of both the slat wing and the main wing. This study revealed for the first time that the ice on the back of the slat wing exhibits a unique double-ridge ice shape， and the formation mechanism of the ice shape was interpreted through numerical analysis. The results and findings can provide valuable references for the design of high-lift and anti-/de-icing devices in the aircraft.
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