摘要
飞机在结冰条件下飞行时可能发生结冰,飞机一旦结冰,会对安全飞行带来较大的隐患,如何降低飞机结冰带来的危害已成为飞机设计研究的重点内容。通过FENSAP-ICE对机翼进行数值模拟,并通过改进Messinger结冰热力学模型模拟更加真实的飞行情况;分析不同飞行环境下,飞机结冰前后机翼气动特性的变化,同时针对机翼设计一套防除冰系统并验证其可行性。结果表明:飞行速度越大,机翼表面的局部水收集系数越大;环境温度会影响机翼结冰的类型和结冰厚度,机翼发生结冰时,其升力系数减小、阻力系数增大,机翼的气动特性受到严重的影响;设计的电热防冰系统可以有效地预防机翼表面结冰,也可以进行周期性除冰。
When the airplane is flying in the icing condition, the surface of airplane is likely to freeze to influence the flight safety. Therefore, the main research contents focus on decreasing the damage caused by aircraft icing. Based on the software of FENSAP-ICE, the numerical simulation of wings is completed. The ice thermodynamics model of Messinger is modified to simulate more realistic flight conditions. The changes of aerodynamic characteristics of wings before and after aircraft icing under different flight conditions are analyzed. Meanwhile, a system of anti-icing and de-icing is designed and the feasibility for wings is verified. The results show that the faster, the flight speed, the greater, the local water collection coefficient of the wing surface. Ambient temperature affects the type and thickness of wing icing. The lift coefficient decreases, the drag coefficient increases and the aerodynamic characteristics of the wing will be deeply influenced when the wing is frozen. The electric heating anti icing system designed can effectively prevent icing on the wing surface and can carry out periodic de-icing.
出处
《航空工程进展》
CSCD
2016年第4期439-446,470,共9页
Advances in Aeronautical Science and Engineering
