机翼展向不同部位结冰对飞机气动力特性影响研究

Study on aerodynamic characteristics of ice accretion in different wing span sections

机翼展向不同部位结冰对飞机气动力特性的影响规律是机翼防除冰系统设计需要考虑的重要因素之一。通过风洞试验方法,将机翼不同部位的模拟冰型加装在飞机模型上进行常规测力试验,研究巡航构型、着陆构型下的机翼展向不同部位结冰后的升力特性、阻力特性、俯仰力矩特性的变化规律。同时通过数值计算的手段,分析机翼不同部位结冰的流场细节特征。研究结果表明,机翼中段结冰对飞机气动力特性影响最为严重,翼根和翼尖结冰影响较小,研究结果为制定高效合理的防除冰系统提供技术依据。

Aerodynamic characteristics of icing on different wing sections are one of the most important factors to be considered for designing anti/de-icing system.Wind tunnel routine force measure tests were carried out to obtain aerodynamic characteristics using simulation ice model on different wing sections of an airplane.Wing leading icing on different wing span sections would lead to different aerodynamic performance losses.Cruise and landing configurations were involved to study the lift,drag and pitch characteristics of the airplane.The results of the research showed that icing in the middle part of the wing lead to the greatest aerodynamic performance losses,and icing at the root and the tip of the wing leads to less aerodynamic performance losses which could be propitious to establish effective and efficient anti/de-icing system.