非结冰气象条件下机翼热气防冰系统数值模拟  

Numerical simulation of a wing hot air anti-icing system in dry air conditions

作　　者：郁嘉[1] 卜雪琴[1,2] 林贵平[1,2] 申晓斌[1,2] 马文涛[1,2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京航空航天大学人机工效与环境控制重点学科实验室,北京100191

出　　处：《空气动力学学报》2016年第5期562-567,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(51206008)

摘　　要：为了在自然结冰飞行前预估飞机防冰系统的性能,减少飞行风险,开展了非结冰气象条件下飞机机翼热气防冰系统的数值模拟研究。数值模拟采用了计算流体力学方法;外部对流传热系数的计算采用附面层积分方法。机翼热气防冰系统表面温度的计算是将蒙皮外部散热热流、内部热气加热热流以及蒙皮导热三者进行热耦合,并进行了改进,改进的方法不要求防冰腔内、外两套网格在重合面网格处一致,是通过双向线性插值将一方面网格信息插值传递到另一方表面网格上,提高了计算效率。In order to evaluate the effectiveness of an ice protection system in natural atmospheric icing conditions and reduce the flight test risks in icing conditions.Numerical analysis and validation for a wing hot-air anti-icing system in dry air conditions are investigated. The computational fluid dynamics （CFD）method was used for the simulation of the wing anti-icing system.The thermal boundary layer integral method was applied to acquire the external convective heat transfer coefficient.Surface equilibrium temperatures were obtained by coupling the external convective heat loss,the internal heat gain and the thermal conductivity through the skin.An improved method was proposed to exchange the values of the surface temperature and heat loads between the internal grid interface and the external grid interface.The method reduced the total cell number of the external flow field and accelerated the calculation speed.

关 键 词：热气防冰系统 机翼 数值模拟 非结冰气象条件 表面温度 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]