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Aircraft icing in flight: Effects of impact of supercooled large droplets

机译：飞行中的飞机结冰：过冷大液滴撞击的影响

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In this study a computational method is presented which simulates the presence of a liquid layer on an airfoil and its effect on splashing of Supercooled Large Droplets (SLD). The thin liquid film is expected to have a significant influence on the impact behaviour of SLD. It will arise when the impacting droplets freeze only partially and leave behind a layer of runback water on top of the ice layer. The liquid film is modelled using the wall shear stress and by assuming a linear velocity profile within the water layer. The shear stress is calculated by coupling an integral boundary-layer method to a potential flow method.udThe SLD splashing model is extended with a deposition model that accounts for impact on a liquid film and includes the solidification time of the droplets. This solidification time is obtained using multiple approaches which are based on either planar solidification or dendritic solidification. Planar solidification is controlled by diffusion and based on the Stefan problem for heat conduction. Dendritic solidification is more rapid and mostly governed by kinetics.udThe comparison of the catching efficiency with experimental results for a NACA-23012 airfoil shows a significant improvement employing the new deposition model. Also, good agreement is found with the experimental results for the ice accretion on a NACA-0012 airfoil.
机译：在这项研究中，提出了一种计算方法，该方法可模拟机翼上液体层的存在及其对过冷大液滴（SLD）飞溅的影响。期望液体薄膜对SLD的冲击行为具有重大影响。当撞击的液滴仅部分冻结并在冰层顶部留下一层流失的水时，就会出现这种情况。使用壁剪切应力并通过假设水层内的线速度分布来对液膜进行建模。通过将积分边界层方法与势流方法耦合来计算剪切应力。 udSLD飞溅模型扩展了沉积模型，该模型考虑了对液膜的影响并包括液滴的凝固时间。该固化时间是使用多种基于平面固化或树枝状固化的方法获得的。平面凝固是通过扩散并基于Stefan问题进行热传导控制的。树突状凝固速度更快，且主要受动力学控制。 ud将捕获效率与NACA-23012机翼的实验结果进行比较表明，采用新的沉积模型可显着改善。而且，发现与NACA-0012机翼上积冰的实验结果吻合良好。

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