机翼结冰过程的数值模拟

杨胜华; 林贵平

机翼结冰过程的数值模拟

北京航空航天大学航空科学与工程学院,北京 100191

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出版历程
- 收稿日期: 2009-12-26
- 修回日期: 2010-03-03
- 刊出日期: 2011-02-28

Numerical simulation of ice accretion on airfoils

School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 为预测飞机机翼结冰的形状,建立了一套采用时间步进法进行结冰过程数值模拟的方法.开发了一个软件框架用于使结冰模拟和网格更新全自动化.基于Messinger的质量和能量守恒方程建立了结冰热力学模型.采用了基于Spalart-Allmaras湍流模型在粗糙壁面的扩展模型来计算表面传热系数.提出了一种新的结冰生长方式.能预测霜冰、明冰及复杂双角冰冰形,并具有模拟长时间结冰的能力.与NACA 0012翼型的冰形试验数据对比发现,计算结果令人满意.
- 飞机结冰 /
- 冰形 /
- 对流传热 /
- 粗糙壁面 /
- 明冰
Abstract: To predict ice shapes on airfoils,a methodology for time-stepping ice accretion simulation was created.A software framework was developed to realize automatic ice accretion calculation and mesh updating process.The ice accretion thermodynamic model was built on Messingers conservation equations for mass and energy.The convective heat transfer coefficient was computed based on an extension of the Spalart-Allmaras turbulence model on rough wall.A new ice growth method was proposed.Test cases show that the present method is capable of simulating long-time rime,glaze ice accretion and the cases with two complex ice horns.Comparison with the experimental ice shape data of a NACA 0012 airfoil shows that the computed results are satisfactory.
- aircraft icing /
- ice shape /
- convective heat transfer /
- rough wall /
- glaze ice

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参考文献(23)

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