某型飞机机翼防冰系统计算分析

Investigations of the bleed air anti-icing system for an aircraft wing

主要针对某型飞机机翼的热气防冰系统计算分析,得到水滴直径变化对撞击极限的影响,飞行马赫数变化对机翼表面换热系数的影响,分析了不同飞行高度湿表面和干表面的温度分布.结果表明水滴撞击区随着水滴直径增加而增大;机翼表面的换热系数随飞行马赫数的增加而增加;在相同计算条件下,干表面温度比湿表面温度要高.对多个典型截面以及其在不同飞行状态的计算结果表明,在给定的计算条件下,4km及7 km时防冰系统工作都是有效的,7 km时表面部分位置湿表面温度低于0℃.

Calculation and analysis for bleed air anti-icing system of an aircraft wing was conducted, Influences of droplet diameter on impinging limits and Mach number on heat transfer coefficient were analyzed. Evaluation of the system＇s effectiveness at different flight height was conducted. The results showed that impinging limits increased with the droplet diameters increasing, heat transfer coefficient of the wing surface increased with the Mach number increasing, and dry temperature of anti-iced surface was higher than wet temperature under the same conditions. Results for several typical cross sections under different flight conditions indicated, for the given parameters, the system was effective at H=4 km and H=7 km, some wet temperature of anti iced surface at H=7 km was lower than 0℃.