抄録
This paper presents the measuring result that the turbulent flow around the wing tip and the aerodynamic sound of NACA0012. Reynolds number based on the chord length of the airfoil and the uniform velocity is 3×1O^5. The airfoil is the lifting condition when the angle of attack is 15 degrees. The results of the velocity fluctuation and the pressure fluctuation showed that the formed vortex at the suction side near the wing tip called secondary vortex is comparatively high fluctuation level. In addition, the secondary vortex doesn't seem to contribute to Strouhal number of 4 to 10.
