摘要
通过粒子图像测速(PIV)技术,在低速风洞中研究了0°~15°攻角和雷诺数分别为1.54×10^5、2.57×10^5和3.59×10^5下NACA64-418翼型的压力性能,并基于γ-Reθ转捩模型分析了翼型表面的流动分离及涡脱落情况。研究表明:NACA64-418翼型具有较大的失速攻角,PIV结果的时均流场和瞬时流场表明,NACA64-418翼型具有较大的失速攻角,随着雷诺数的增加,失速攻角变小;从翼型壁面回流区可以看出γ-Reθ转捩模型可以准确评估翼型表面从层流到湍流流动的变化;数值结果与实验结果进行比较,验证了γ-Reθ转捩模型的预测是准确的。
The pressure performance of NACA64-418 airfoil at 0~15 degree angles of attack and Reynolds numbers of 1.54×10^5,2.57×10^5 and 3.59×10^5 were studied by particle image velocimetry(PIV)in a low-speed wind tunnel.The flow separation and vortex shedding on the airfoil surface were analyzed based on theγ-Reθtransition model.The results show that the NACA64-418 airfoil has a large stall angle of attack.The time-averaged flow field and instantaneous flow field of PIV results show that the NACA64-418 airfoil has a large stall angle of attack.With the increase of Reynolds number,the stall angle of attack decreases.It is verified that the prediction ofγ-Reθtransition model is accurate.
作者
石建伟
常方圆
宋文武
肖姚
SHI Jian-wei;CHANG Fang-yuan;SONG Wen-wu;XIAO Yao(School of Energy and power Engineer,Xihua University,Chengdu,China,610039;Chongqing Chongtong Chengfei New Materials Co.,Ltd.,Chongqing,China,400000)
出处
《热能动力工程》
CAS
CSCD
北大核心
2020年第2期254-264,共11页
Journal of Engineering for Thermal Energy and Power
基金
国家自然科学基金资助项目四川省科技厅应用基础研究项目(2016JY0187)
四川省教育厅培育项目(14CZ013)
西华大学流体及动力机械教育部重点实验室开放基金(szjj2015-037)。
