Aerodynamic Characteristics of the 10-Percent-Thick NASA Supercritical Airfoil 33 Designed for a Normal-Force Coefficient of 0.7

This report documents the experimental aerodynamic characteristics of a 10-percent-thick supercritical airfoil based on an off-design sonic-pressure plateau criterion. The airfoil was developed for a design normal-force coefficient of 0.7 and identified as supercritical airfoil 33. The results are compared with those of the earlier 10-percent-thick supercritical airfoil 31 with the same design normal-force coefficient. Comparisons are also made between experimental and theoretical characteristics and composite drag rise characteristics derived for a full scale Reynolds number of 40 million.