NACA0012の後縁を切断した鈍い後縁の翼の揚力特性 [in Japanese] Lift Characteristic of Blunt Trailing Edge Aerofoils Formed by Cutting the Rear of NACA0012 [in Japanese]
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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.
- Aeronautical and Space Sciences Japan
Aeronautical and Space Sciences Japan 45(516), 62-66, 1997-01
The Japan Society for Aeronautical and Space Sciences