翼型表面结冰准定常数值模拟  

Quasi-steady numerical simulation of ice accretion on airfoil

作　　者：常士楠[1] 杨秋明[1] 李延[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《空气动力学学报》2011年第3期302-308,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(10872020;11072019)

摘　　要：对翼型表面的结冰过程进行了准定常数值模拟。在每个时间步长内完成网格随着壁面边界的移动而更新、周围流场和水滴撞击特性重新计算、冰形计算及壁面边界的重构工作,如此循环直至所需的结冰计算时间。采用拉格朗日轨迹追踪法获得水滴撞击特性,应用考虑壁面粗糙度影响的边界层积分法计算壁面的对流换热系数,在此基础上求解Messinger结冰热力学模型,冰层始终沿壁面外法线方向生长。对NACA0012翼型在不同环境下生成的三种典型冰形进行了预测,并与实验结果进行了比较,表明本文所述方法的有效性。Quasi-steady method was applied to simulate the process of ice accretion on airfoil.Within each time step,mesh was refreshed following the boundary moving,flow field and droplet impingement characteristic were calculated again,ice shape and boundary were newly formed.They were done repeatedly until the needed ice accretion time.Lagrangian method was applied to calculate the droplet impingement characteristic,integral boundary layer method considering roughness effect was employed to calculate convective heat transfer coefficient on the wall.Messinger ice accretion model was solved and ice grew along the direction normal to the airfoil surface.Three typical ice shapes on NACA0012 airfoil at different environmental temperatures were predicted and compared with experimental results.It indicates that the method expatiated in this paper is applicable and effective.

关 键 词：结冰模拟 边界移动 水滴轨迹 边界层积分法 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]