The Effects of Roughness at High Reynolds Numbers on the Lift and Drag Characteristics of Three Thick Airfoils


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In connection with studies of airfoils applicable to large high-speed aircraft, the effects of roughness on three 22-percent-thick airfoils were investigated. The tests were made over a range of Reynolds numbers from about 6,000,000 to 26,000,000 for the airfoils smooth and with roughness strips applied to the surfaces. The results indicated that for the roughened models the scale effect was generally favorable.




NACA Wartime Report


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Index of NACA Technical Publications


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Wartime Report


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Wartime Report


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Theory of Wing Sections


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Concise compilation of subsonic aerodynamic characteristics of NACA wing sections, plus description of theory. 350 pages of tables.










Effects of Roughness at High Reynolds Numbers on the Lift and Drag Characteristics of Three Thick Airfoils


Book Description

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