Abstract
In this paper, static pressure fluctuation and velocity fluctuation around NACA0012 airfoil are measured by using the pressure probe and the hotwire anemometer in order to clarify flow structures and unsteady behavior of airfoil tip flows. The Reynolds number based on the chord length of the airfoil and uniform flow velocity is 8×10^4 and the airfoil is under the high lift condition. In the test section, the airfoil is vertically installed and the pressure probe is installed in the flow from downstream of the airfoil. Static pressure distributions and velocity distributions indicate the fluctuation regions caused by the primary vortex and the secondary vortex are outer of tip vortex center.
