1112 翼端渦流れの挙動と発生する騒音の研究
詳細
In this paper, three components of flow velocity around NACA0012 airfoil in some two dimensional sections are measured by using the stereo P1V method in order to clarify flow structures and unsteady behavior of airfoil tip flows contributed to tip flow noise. The Reynolds number based on the chord length of the airfoil and uniform flow velocity is 1.3×10^5 and 3.3×10^4, and the airfoil is under the high lift condition. Band pass filtered characteristics with velocity distributions are shown.
