摘要
为研究带后掠角机翼的结冰数值模拟方法,通过建立三维结冰初始水膜模型以及结冰增长模型,对带后掠角的机翼进行结冰数值仿真。为验证模型的准确性,使用FENSAP-ICE软件进行同工况数值仿真,并且设计加工了30°后掠角的NACA0012翼型进行结冰风洞实验。结果表明:本模型能够对后掠翼的明冰工况进行仿真,仿真冰型与FENSAP-ICE冰型轮廓大致相同;所计算的冰型与实验结果吻合较好,在冰角处的形状有差异,但冰生长的总体趋势和大致结冰量与实验一致,沿展向不同截面冰型增长趋势也与实验大致一致。可见后掠翼结冰数值模拟方法能够进行后掠翼结冰外形的计算。
In order to study the numerical simulation method on the ice accretion of the swept wing,an ice growth model considering the initial water film was established to do numerical simulation of swept wing model.In order to verify the accuracy of the model,FENSAP-ICE was used to do the numerical simulation with the same working condition,and the swept wing model NACA0012 with the sweep angle of 30°was designed to do the icing wind tunnel experiment.The results show that this model can do numerical simulation of the swept wing at glaze ice conditions.The ice profiles are roughly the same with FENSAP-ICE results.The ice forms calculated are in good agreement with the experimental results,the shapes at the ice angles are a little bit different but the overall trend of ice growth and the approximate amount of ice accretion are consistent with the experimental results.The growth trend of ice forming at different sections along the spreading direction is also roughly consistent with the experimental results.It can be seen that the numerical simulation method of swept wing icing accretion is effective.
作者
姜寒
朱春玲
JIANG Han;ZHU Chun-ling(College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
出处
《科学技术与工程》
北大核心
2021年第21期9123-9128,共6页
Science Technology and Engineering
基金
国家自然科学基金(51806105,11832012)
江苏省自然科学基金(BK20180442)
973计划(2015CB755800)
江苏省科技重点研发计划(BE2016006-5)。
关键词
飞机结冰
三维
后掠翼
明冰
airfoil icing
three-dimensional
swept wing
glaze ice
