一种用于飞机结冰的海绵冰模型及应用  

A spongy icing model for aircraft icing and application

作　　者：李鑫[1] 白俊强[1] 王昆[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空动力学报》2013年第11期2419-2429,共11页Journal of Aerospace Power

摘　　要：基于两相流理论,采用欧拉法对飞机结冰进行数值模拟,在空气流场速度分布的基础上,求解水滴流场,得到水滴收集率和撞击极限.结果表明:欧拉法比拉格朗日法在计算水滴收集效率和撞击极限方面有优势,尤其是在较大的水滴平均等效直径情况下.对翼型的冰形和圆柱表面的温度预测数据和实验数据进行对比,圆柱冰形厚度误差在15.0%之内,计算结果与实验结果吻合较好,同时表明结冰模型是有效可行的.An Eulerian method to simulate aircraft icing was developed based on tWO phase flow theory, and the water collection efficiency and impingement limits were solved based on the velocity distribution of air flow. Results show that Eulerian method performs better on water collection efficiency and impingement limit than Lagrangian method, espe cially under large median volumetric diameter conditions. The predicted ice shape and surface temperature were compared with experimental results, the thickness error of the cylinder ice shape was less than 15.0% and the computational results were in good agreement with the experiment data, showing that the icing model and twophase flow simulation are feasible and effective.

关 键 词：海绵冰模型 数值模拟 N—S方程 欧拉两相流法 飞机结冰 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]