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建立了利用欧拉法求解水滴撞击特性的方法,并基于Messinger质量和能量守恒方程建立了热载荷计算模型,以某型飞机三维水平尾翼为研究对象,展开了撞击特性和热载荷的计算.结果显示水平尾翼的局部水收集系数极值从翼根到翼尖逐渐增加,不同截面水滴收集系数的分布为设计防冰系统范围提供了依据.驻点附近及机翼上、下表面各存在一个热载荷较大的区域,进而确定该尾翼电加热防冰分为3个区域:中间连续加热区和上、下表面驻点附近的各一个间断加热区.
A method of calculating the impact of droplet by using Euler method was established and a heat load calculation model was established based on Messinger mass and energy conservation equations. The impact characteristics and thermal load were calculated by taking a three-dimensional tailplane of a certain aircraft as the research object. It is shown that the extreme value of the local water collection coefficient increases from wing root to wing tip, and the distribution of water collection coefficient in different sections provides the basis for designing the range of anti-ice system. Load larger area, and then determine the tail of the anti-ice electric heating is divided into three areas: the middle of the continuous heating zone and the upper and lower surface near the stagnation of a discontinuous heating zone.