NACA0012の後縁を切断した鈍い後縁の翼の揚力特性

抄録

The lift characteristic of blunt trailing edge NACA0012 aerofoil is investigated with a Göttingen type low speed wind tunnel and the results are compared with discrete vortices calculation method. The balance test is performed at Re=3.5×10⁵ and the pressure distributions over the wing surface are measured at Re=4.7×10⁵. The followings are known: (1) the lift slope of a blunt trailing edge aerofoil is greater than the one of the sharp trailing edge NACA0012, (2) the pressure distributions upstream to the trailing edge cutting point are little changed by the cutting, and (3) the lift slope of a blunt trailing edge aerofoil is higher than the sharp trailing edge aerofoil for the same thickness ratio.