牛顿型飞机除冰防冰液流变特性风洞试验与数值模拟研究

For safety in flight, it is an important means for the Civil Aviation to use aircraft deicing/anti-icing fluid which will prevent to ice on the aircraft surface in winter. The flow characteristics of deicing/anti-icing fluid has a very important impact on the deicing anti-icing effect and aircraft aerodynamics characteristics under different conditions. The wind tunnel tests and numerical simulation will be used in this project. Not only the effect of the atmospheric parameters, flight parameters, deicing/anti-icing fluid properties on the Newtonian deicing/anti-icing fluid flow properties and the displacement thickness of the boundary layer wil be investigated, but also the effect of presence of deicing/anti-icing fluid on the wing aerodynamic performance wil be researched. The project will provide a theoretical basis and technical support to improve the deicing/anti-icing fluid performance and aircraft security margin.

利用飞机除冰防冰液防止飞机表面积冰是民航冬季运行安全的重要保障手段。不同条件下除冰防冰液的流变特性对除冰防冰效果及飞机的空气动力学特性有着非常重要的影响。本项目拟采用风洞试验和数值模拟相结合的方法，研究大气参数、飞行参数、除冰防冰液属性对牛顿型除冰防冰液流变特性和附面层位移厚度的影响规律，及除冰防冰液的存在对机翼气动性能的影响，为提高除冰防冰液性能和飞机安全保障裕度提供理论依据和技术支持。

本文介绍了牛顿型飞机除冰防冰液流变特性的试验与数值模拟方法，然后对不同条件下除冰防冰液流变特性进行了试验与数值模拟分析。结果表明，试验方案可靠，试验结果能基本反应除冰防冰液流变特性基本规律；在验证数值模拟方法可靠性后，将其应用于除冰防冰液流变特性的计算，分析了其附面层位移厚度的变化规律，同时考察了来流速度对其流变特性的影响。