1956•NASA STI Repository (National Aeronautics and Space Administration)Requires access
Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0
Bernard N Daley, Richard S Dick
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Abstract
Report presenting tests of a group of related NACA airfoil sections varying in maximum thickness, design lift coefficient, and thickness distribution in a two-dimensional open-throat wind tunnel at a range of Mach numbers. Normal-force, drag, and pitching-moment coefficients are presented with representative schileren photographs and pressure-distribution diagrams.