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采用数值计算和结冰风洞实验相结合的手段,对某运输机机翼剖面缩比翼型的结冰特性进行了研究.结冰实验在气动中心0.3m×0.2m结冰风洞中进行,实验模型为弦长0.18m的层流翼型.翼型的绕流流场通过求解低速黏流的时均Navier-Stokes(N-S)方程得到,采用拉格朗日法计算水滴撞击特性,在此基础上,求解结冰热力学模型,获得结冰外形.对计算和实验结果进行了对比分析,发现虽然局部冰形轮廓还存在差异,但计算和实验得到的冰形在结冰极限、冰形体积和主要特征等方面基本一致.研究显示:在结冰的初始阶段,翼型前缘的冰形较规则,随着结冰时间的增加,冰形逐渐变得不规则;翼型下表面冰体前部为明冰,冰体后部、尤其是结冰极限附近则呈现典型的霜冰特征;翼型上表面的结冰范围远小于下表面,在结冰极限附近也不再有明显的霜冰.
In this paper, the icing characteristics of airfoil with reduced cross-section of a transport aircraft are studied by means of numerical calculation and icing wind tunnel experiment.The freezing experiment is carried out in a wind tunnel of 0.3m × 0.2m in the aerodynamic center, and the experiment The model is a laminar airfoil with a chord length of 0.18 m.The flow field around the airfoil is obtained by solving the Navier-Stokes (NS) equation for hour-velocity viscous flow over time, using the Lagrange method to calculate the droplet impact characteristics, , The icing thermodynamic model was solved and the icing profile was obtained.Comparison and analysis of the calculated and experimental results showed that although there were some differences in the local ice shape profiles, the calculated and experimental ice shapes had no significant difference in the icing limit, ice volume and Main characteristics, etc. The research shows that in the initial stage of icing, the ice shape of the leading edge of the airfoil is more regular, and as the ice time increases, the ice shape gradually becomes irregular; The Ministry of ice is the ice, the back of the ice body, in particular the typical frost ice characteristics near the icing limit; the upper surface of the airfoil the icing area is much smaller than the lower surface, there is no significant frost ice in the vicinity of the icing limit .