三维翼面结冰过程及其影响数值研究

为得到三维机翼及翼身尾构型在结冰条件大气中的结冰过程和影响,采用结构化网格对M6机翼和翼身尾构结冰过程进行数值模拟,对飞机结冰过程的数值模拟采用欧拉两相流法求解水滴撞击特性,基于Messinger热力学模型模拟冰形增长过程,对其水滴撞击特性、结冰形状及结冰后对气动特性影响进行研究.分析结果可得:机翼展向,随着弦长变小,结冰量逐渐增多,尤其对大展弦比机翼更为明显.同时机身前端迎风面也是比较容易积冰的区域.

Numerical simulation of icing accretion and influence on three-dimensional wing configuration

The structured grid was used to numerically simulate the icing accretion of M6 wing and wing-body-tail configuration to get the icing process and influence under icing weather conditions. Euler two-plase flow methods was used to solve droplets impingement characteristics for the simulation of icing process. Thermodynamic model of icing growth was based on the Messinger model. Then, it was researched that the droplet impingment, shape of the iced wing and the influence on aerodynamic characteristics. The result showed the mass of icing increased with the spanwise chord reduction, especially for high-aspect-ratio wing. Moreover, the front of fuselage was also vulnerable to serious icing.