某型飞机机翼防冰系统计算分析

常士楠; 袁美名; 霍西恒; 张泉

某型飞机机翼防冰系统计算分析

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
陕西飞机工业集团设计院, 汉中 723213

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- 被引次数: 0
出版历程
- 收稿日期: 2008-01-03
- 修回日期: 2008-05-06
- 刊出日期: 2008-06-28

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

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
The Aircraft Design Institute, Shanxi Aircraft Industry Group, Hanzhong 723213, China

摘要

摘要: 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7km时防冰系统工作都是有效的,7km时表面部分位置湿表面温度低于0℃.
- 航空、航天推进系统 /
- 机翼 /
- 热气防冰系统 /
- 水滴撞击特性 /
- 传热分析 /
- 湿表面温度
Abstract: 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 than0 ℃.
- aerospace propulsion system /
- aircraft wing /
- bleed air anti-icing system /
- droplet impingement /
- heat transfer analysis /
- wet surface temperature

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参考文献(10)

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