乱れの中に置かれた翼端渦から発生する空力騒音に関する研究

抄録

In this study, to investigate the effect of inflow turbulence on the flow structure around the wing tip, static pressure fluctuation around airfoil was measured when the inflow turbulence was changed with five types of turbulence grids. The model had the NACA0012 wing section, chord length of 60 mm and a wingspan length of 120 mm. The Reynolds number based on the chord length and inflow velocity was 1 × 105, and the angle of attack of the wing was 13 °. The measurement range was 20 mm × 20 mm at the position of X/C = 1.47 with the mainstream direction as X from the leading edge of the wing. In the test section, the airfoil was vertically installed and the pressure probe was installed in the flow from downstream of the airfoil. As a result, the region with high static pressure fluctuation was distributed from the center of the tip vortex to the outside when the turbulence intensity and turbulence length scale were low, but it also spread to the center of the vortex as they increased.