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| NACA Report No. 964 ： ウィキペディア英語版 |
NACA Report No. 964
NACA Report No. 964 - The effects of variations in Reynolds number between 3.0 x 106 and 25.0 x 106 upon the aerodynamic characteristics of a number of NACA 6-series airfoil sections was published by the United States National Advisory Committee for Aeronautics in 1950. It contained a series of graphs showing the resulting lift and drag of several NACA 6-series airfoil sections from tests performed in a variable-density wind tunnel, in which the Reynolds number (RN) was set at three different values.
==Summary==
Results are presented of an investigation made to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil sections at RN of 15.0, 20.0, and 25.0 million. Also presented are data from NACA Rep. 824 for the same airfoils at RN of 3.0, 6.0, and 9.0 million. The airfoils selected represent sections having variations in the airfoil thickness, thickness form, and camber. The characteristics of an airfoil with a split flap were determined in one instance, as was the effect of surface roughness. Qualitative explanations in terms of flow behavior are advanced for the observed types of scale effect.
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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