抄録
In this paper, three components of flow velocity around NACA0012 airfoil in some two dimensional sections are measured by using the stereo PIV method in order to clarify three dimensional vertical structures and unsteady behavior of airfoil tip flows. The Reynolds number based on the chord length of the airfoil and uniform flow velocity is 1.33X105, and the airfoil is under the high lift condition. The results shows primary vortex on the suction surface and secondary vortex on the airfoil tip are high fluctuated.
