The cumulative effects of roughness and Reynolds number on NACA 0015 airfoil section characteristics
Lewis, Kevin Wayne
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In this study, wind tunnel tests were made on a NACA 0015 airfoil section to examine the combination of scale and surface roughness effects. Reynolds numbers of 110,000 and 220,000 were used to determine scale effects. Roughness effects were obtained by applying roughness elements with heights of 0.111, 0.282, and 0.564 percent of the airfoil chord length. it was found that each combination of Reynolds number and roughness results in a unique set of lift and drag coefficients for a given angle of attack.