Effect of deformation and breakup characteristic on supercooled large droplet icing process

被引：0
|
作者：
Sang W. [1 ]
Cai Y. [1 ]
Lu T. [2 ]
机构：
[1] School of Aeronautics, Northwestern Polytechnical University, Xi'an
[2] Institute of Flight, Chinese Flight Test Establishment, Xi'an
来源：
| 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 32期
关键词：
Aircraft icing; Droplets deformation and breakup; Finite volume method; Supercooled large droplet; Taylor analogy method;
D O I：
10.13224/j.cnki.jasp.2017.07.001
中图分类号：
学科分类号：
摘要：
To reveal and master the effects of the droplets deformation and breakup under supercooled large droplet (SLD) conditions, a numerical solver was developed to simulate the ice accretion. The ice accretion on the NACA 0012 airfoil was predicted. For the SLD movement, the droplet deformation and breakup process was investigated using a dynamically varying drag model and Taylor analogy method. Using the above methods, the numerical simulation of ice accretion and icing effects at the deformation and breakup of SLD was performed. These numerical results were compared with the computational and experimental data in several past literatures. The results are in good agreement with experimental data, indicating that the models and methods are feasible and effective. And the comparative results show that accounting of deformation and breakup has made significant improvement to the simulation of the droplet trajectory and ice shape distribution for the SLD icing prediction. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1537 / 1544
页数：7
相关论文
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