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Low-speed tests of five NACA 66-series airfoils having mean lines designed to give high critical Mach numbers
Albert E Von Doenhoff, Louis S Stivers, James M. O'Connor
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Abstract
Report presenting an investigation of the possibility of developing an airfoil to carry lift without decreasing the critical Mach number below that of the basic thickness form at zero lift. Low-speed testing of five NACA 66-series airfoil sections with a thickness-chord ratio of 0.16 was carried out in the two-dimensional low-turbulence pressure tunnel. Results regarding the design lift coefficient, maximum lift coefficient, low-drag range, and pitching-moment coefficients are provided.