摘要
介绍了直升机在悬停状态下 ,求解旋翼水滴撞击特性的数值方法 .该方法根据直升机悬停状态下的准定常特性 ,对旋翼运动模型进行简化 ,并在对绕桨叶运动的气流场计算的基础上 ,采用有限差分方法求解水滴运动方程 ,得到水滴运动轨迹 .进而 ,确定了水滴对旋翼表面的撞击特性参数 ,为旋翼防冰系统设计提供条件 .最后 ,对NACA0 0 1
The numerical method of determining the water droplet impingement property of the rotor blade of helicopter in hover was studied. According to the quasi-steady property, the rotor model in hover was simplified. Based on the calculation of flow field around the blade, the droplet trajectories were obtained by the finite difference method. The parameters of droplet impingement on blade were given, which provided the conditions for rotor antiicing or deicing system design. The impingement properties of NACA0012 rotor blade were presented as an example.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第11期1055-1058,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
"十五"预研基金资助项目
关键词
防冰系统
除冰系统
旋翼
水滴撞击特性
水滴轨迹
Finite difference method
Ice control
Impact resistance
Impellers
Numerical methods
Water
