The variation with Reynolds number of pressure distribution over an airfoil section (1938)
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70 REPORT NO. 013—NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS … 0000 0 0 0 08 -8 16 84 -16 Angle of attack, c(t ,deg. Figures.—Lift curves for the N. A. 0. A.44I2alrfotlat several values of ths Reynold's Number. In order to keep the pressure measurements as ac- curate as possible, it was necessary to obtain large 2.0 deflections of the manometer liquids, -which…
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