水滴撞击飞溅效应对过冷大水滴结冰影响研究

发布时间：2018-06-02 22:06

本文选题：飞机结冰 + 过冷大水滴　；参考：《西北工业大学学报》2016年05期

【摘要】：过冷大水滴(SLD)结冰的结冰量较大、位置靠后且容易形成复杂冰型,对飞机气动性能和飞行安全具有更大危害性。在结冰过程数值模拟的基础上,针对SLD条件下水滴撞击的飞溅效应及其对成冰过程影响进行研究。采用结构化网格和中心有限体积法求解N-S方程获得空气流场,运用拉格朗日法求解水滴流场,基于改进的Messinger热力学模型进行翼面结冰模拟。对SLD结冰,采用飞溅碰撞模型,分析了水滴飞溅现象及其对SLD结冰过程的影响,完成了典型翼型结冰算例的数值模拟和分析讨论,与参考文献和试验结果的对比,说明了文中计算模型及计算方法在模拟SLD结冰的撞击飞溅效应时是可行和正确的,获得的影响规律和结论对于深入研究SLD结冰具有重要的参考价值。
[Abstract]:The supercooled large water droplet (SLD) icing has a large amount of ice formation, which is more harmful to aircraft aerodynamic performance and flight safety due to its position backward and easy to form complex ice form. Based on the numerical simulation of ice forming process, the splash effect of water droplet impact under SLD and its influence on the ice forming process were studied. The air flow field is obtained by solving N-S equation with structured grid and center finite volume method, and the droplet flow field is solved by Lagrangian method. The icing simulation of wing surface is carried out based on the improved Messinger thermodynamic model. For SLD icing, the splash collision model is used to analyze the droplet splash phenomenon and its influence on the SLD icing process. The numerical simulation and analysis of typical airfoil icing examples are completed, which are compared with references and experimental results. It is shown that the calculation model and calculation method are feasible and correct in simulating the impingement splash effect of SLD icing, and the influence rules and conclusions obtained are of important reference value for the further study of SLD icing.
【作者单位】：西北工业大学航空学院;中国飞行试验研究院飞行部;
【基金】：国家自然科学基金(11072201) 航空科学基金(2015ZA53007)资助
【分类号】：V321.229

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