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.