摘要
时间步长是影响飞机结冰数值模拟精度的重要参数之一。本文通过求解雷诺时均N-S方程,湍流模型采用κ-ε两方程模型,获得空气流场,求解水滴运动轨迹方程获得水滴撞击特性,基于Messinger热力学模型求解能量和质量守恒方程计算冰形,并采用扇形分区法,更新机翼前缘结冰区网格,保持网格拓扑结构不变,实现多时间步长结冰数值计算。比较了采用单时间步长法和多时间步长法对翼型表面结冰增长数值模拟的计算结果,并与冰风洞试验数据及LEWICE预测数据进行对比。在此基础上,计算分析了不同时间步长对部件表面的结冰冰形的影响。结果表明,只有采用多时间步长法进行飞机结冰数值模拟才是有效的,并且存在一个合适的时间步长,既满足计算精度要求,又能提高计算效率。
Time-step is one of the most important parameters which affect the accuraey of ice accretion. Flow field is obtained by solving time averaged N-S equations with k-ε turbulence model, droplet impingement characteristics are acquired by calculating the droplet trajectories, and ice shape is calculated with solving thermodynamic mass and energy balance equations based on Messinger model. Besides, grid around wing leading is reconstructed using sectorial partition method. In this way, ice shape with multi time-step method is calculated. Single time-step and multi time-step method with various time steps are used to simulate aircraft icing separately. The ~suhs are compared with IRT data and the computational data of LEWICE, which illustrates that it is necessary to use multi time-step approach and a reasonable time step exists to simulate aircraft icing for a specify geometry.
出处
《世界科技研究与发展》
CSCD
2011年第5期829-835,共7页
World Sci-Tech R&D
关键词
数值模拟
飞机结冰
时间步长
网格重构
numerical simulation
aircraft icing
time step
grid reconstruction
