The effects of variations in Reynolds number between 3.0 x 10 to the power 6 and 25.0 x 10 to the power 6 upon the aerodynamic characteristics of a number of NACA 6-series airfoil sections

Laurence K. Loftin, William J. Bursnall
naca-tn-1773
Dec 1948


Results are presented of an investigation made to determine the two-dimensional lift and drag characteristics of nine NACA 6-series airfoil sections at Reynolds numbers of 15.0 X 10 to the power 6, 20.0 X 10 to the power 6, and 25.0 X 10 to the power 6. Also presented are data from NACA Rep. No. 824 for the same airfoils at Reynolds numbers of 3.0 X 10 to the power 6, 6.0 X 10 to the power 6, and 9.0 X 10 to the power 6. The airfoils selected represent sections having variations in the airfoil thickness, thickness form, and camber.

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