摘要
提出一种翼型表面明冰的数值模拟方法.基于欧拉两相流理论,建立空气、水滴两相流控制方程;提出一种可穿透型壁面边界模拟水滴对翼型表面的撞击;采用考虑了粗糙度影响的边界层积分法求解结冰表面的对流换热特性,基于经典Messinger模型提出明冰数值模拟的热力学模型;利用冰层时间推进法模拟积冰过程,采用积冰法向生长假设生成积冰外形.对NACA 0012翼型在不同环境温度下的明冰冰形进行了预测,并与实验结果进行了对比.
An Eulerian method to numerically simulate glaze ice accretions on an airfoil has been presented. Based on two-phase flow theory, the governing equations of the airflow and droplets were established. A permeable wall was proposed to simulate the droplet impingement on the airfoil surface. An integral boundary layer method, modified to consider the roughness effect, was employed to evaluate the convective heat transfer coefficient. The thermodynamic model for glaze ice accretions was presented by performing the mass and thermal balances. The process of ice accretions was simulated with the assumption that ice accumulates layer-by-layer, and the ice shape was built with the assumption that ice grows in the direction normal to the airfoil surface. The glaze ice accretions on a NACA 0012 airfoil at different environmental temperatures were investigated, while the predicted results and experimental data were compared, indicating that the simulated method presented in this paper is feasible and effective.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期91-97,共7页
Journal of Aerospace Power
关键词
明冰
数值模拟
两相流
水滴
粗糙度
glaze ice
numerical simulation
two-phase flows
droplet
roughness
