机翼表面结冰热力学模型

THERMODYNAMICAL MODEL OF ICE ACCRETION ON AIRFOILS

基于Messinger控制体的思想建立了翼型表面的冰生长热力学模型,论述了模型的求解方法;采用边界层积分法计算LHTC(Local Heat Transfer Coefficient),并嵌入了粗糙度对表面换热的影响;计算得到的LHTC与文献中的结果做了比较验证。本文编制了冰形计算程序模块,集成到自主开发的预测软件中,模拟了不同结冰气象条件下,NACA0012翼型在4°攻角时表面槽状冰、混合冰、楔形冰的形成。数值模拟的结果与文献中提供的实验结果吻合良好,表明本文所用模型及方法可行且有效.

A thermodynamical model of ice accretion on airfoils is established base on Messinger＇ s theory about control volume. And solutions for governing equations of the model are elaborated. The integral boundary layer Method was carried out to account for surface roughness in the calculation of the local heat transfer coefficient （LHTC）. Results of the LHTC of this paper were compared with results of references. This paper programmed a computational procedure module of thermodynamic characteristics and iced geometry, which was then integrated in the predicting-software developed independently. Under different atmospheric conditions, ice accretion （glaze, mixed and rime ice accretion）on the NACA0012 airfoil at a 4° angle of attack ,were simulated in this paper. The comparison between the results of this paper and the experimental data as well as LEWICE code indicates that the current approach is applicable and effective.