热气防冰参数对机翼表面溢流结冰的影响研究

机翼热气防冰数值模拟中，根据N-S方程求解流场，用Euler法获得水滴撞击特性，通过蒙皮导热将求解得到的内外流场进行耦合传热并达到稳定后，开始模拟结冰，来进行机翼热气防冰及形成溢流结冰的数值计算。计算结果表明，热空气防冰数值模拟是可行和合理的。采用数值模拟方法对机翼热空气防冰过程进行了模拟，得到了由于引气温度不足或机翼热空气保护面积不同而导致的不同溢冰高度和位置。分析了供气温度、防冰区域对翼面溢流冰形成的影响。结果表明：供气温度直接正向影响热交换后蒙皮表面温度。供气温度越低，溢流冰形高度越高，对气动特性影响也越大；热防护区域范围对溢流结冰结果也会产生影响，热防护区域越大，冻结位置距离驻点越远，而且冰形高度越低，对气动特性影响也越弱。

Influence of hot air anti-icing parameters on the icing of wing surface overflow

In the numerical simulation process of wing hot air anti-icing, the flow field is solved according to the Navier Stokes equation, and the water droplet impact characteristics are solved by the Euler method, and the solved internal and external flow fields are coupled with heat transfer through the skin heat conduction to achieve stability, and then the simulation of icing is started to carry out the numerical calculation of wing hot air anti-icing and overflow ice formation. The calculation results show that the numerical simulation of hot air anti-icing is feasible and reasonable. In this paper, the numerical simulation method was used to simulate the anti-icing process of wing hot air, and the different ice overflow height and locations caused by insufficient bleeding air temperature or different wing hot air protection area were obtained. The influence of the bleeding air temperature and the anti-icing area on the formation of wing overflow ice was analyzed. The results show that the bleeding air temperature directly and positively affects the skin surface temperature after heat exchange. The lower the bleeding air temperature is, the higher the overflow ice is, and the greater the influence on the lift is. The scope of the hot air protection area will also affect the overflow icing results. The larger the hot air protection area is, the farther the overflow ice is, and the lower the ice height is, the weaker the impact on the lift is.