后掠翼热气防冰系统数值仿真  

Numerical Simulation of a Swept Wing Hot-air Anti-icing System

作　　者：侯盼雪[1] 林贵平[1] 卜雪琴[1] 申晓斌[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院人机工效与环境控制重点学科实验室,北京100191

出　　处：《航空学报》2012年第5期809-817,共9页Acta Aeronautica et Astronautica Sinica

基　　金：“凡舟”青年科研基金（20100501）

摘　　要：对后掠翼热气防冰系统的表面温度进行了数值仿真研究。用欧拉方法计算局部水收集系数,外部对流换热系数用附面层积分法计算,蒙皮导热和内部换热用计算流体力学（CFD）方法计算,用基于FLUENT的用户自定义函数（UDF）方法将外部换热、蒙皮导热和内部换热三者耦合求解,实现了热流边界条件的自动加载和温度的自动更新。通过对ARJ21-700机翼防冰系统性能的计算,说明所研究的计算方法能对三维后掠翼热气防冰系统作出总体性能的评估和局部性能的评价,为自然结冰条件下飞机的飞行试验提供依据,从而大大降低飞行试验风险。The surface temperature of a swept wing hot-air anti-icing system is calculated. The Eulerian method is used for the calculation of the local water collection efficiency. The external heat transfer coefficient is computed using an integrated boun-dary layer method, and the thermal conduction in the wing skin and the internal heat flow are computed using computational fluid dynamics（OFD） method. By means of the commercial software package FLUENT and its user defined functions （UDF;）, the external heat flux, the thermal conduction in the wing skin and the internal heat flux are integrated tightly. At the same time, the heat flux boundary conditions and the surface temperature are updated automatically. The calculation of the ARJ21-700 wing anti-icing system by this method demonstrates that the method can assess the performance of a swept wing and supply the foundation for flight test in natural icing conditions.

关 键 词：后掠翼 热气防冰系统 热耦合 表面温度 数值仿真 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]