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-Reθ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－Reθ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－Reθ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 the γ-Reθ transition 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 of γ－Reθ transition model is accurate.

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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）