Results show the airfoil to have good drag rise characteristics over a wide range of normal-force coefficients with no measurable shock losses up to the Mach numbers at which drag divergence occurred for normal-force coefficients up to 0.7. The airfoil had a design normal-force coefficient of 0.7 and was identified as supercritical airfoil 33. Comparisons are also made between experimental and theoretical characteristics and composite drag rise characteristics derived for a full scale Reynolds number of 40 million.Īerodynamic characteristics of the 10-percent- thick NASA supercritical airfoil 33 designed for a normal-force coefficient of 0.7Ī 10-percent- thick supercritical airfoil based on an off-design sonic-pressure plateau criterion was developed and experimental aerodynamic characteristics measured. The results are compared with those of the family related 10 percent thick supercritical airfoil 33. ![]() The design normal force coefficient was 0.7. This report documents the experimental aerodynamic characteristics of a 14 percent thick supercritical airfoil based on an off design sonic pressure plateau criterion. ![]() Integrated section force and moment data, surface pressure distributions, and typical wake survey profiles are presented.Īerodynamic Characteristics of a 14-Percent- Thick NASA Supercritical Airfoil Designed for a Normal-Force Coefficient of 0.7 The drag divergence Mach number of the improved supercritical airfoil ( airfoil 26a) varied from approximately 0.82 at a normal force coefficient to of 0.30, to 0.78 at a normal force coefficient of 0.80 with no drag creep evident. Refinements in a 10 percent thick supercritical airfoil produced improvements in the overall drag characteristics at normal force coefficients from about 0.30 to 0.65 compared with earlier supercritical airfoils which were developed for a normal force coefficient of 0.7. The Mach numbers at which drag diverges were delayed for airfoil 31 at normal force coefficients up to about 0.6 (by approximately 0.01 and 0.02 at normal force coefficients of 0.4 and 0.6, respectively) but drag divergence occurred at slightly lower Mach numbers at higher normal force coefficients.Īerodynamic characteristics of an improved 10-percent- thick NASA supercritical airfoil. Substantial reductions in the drag levels preceding drag divergence were also achieved at all normal force coefficients. ![]() Drag creep was practically eliminated at normal force coefficients between about 0.4 and 0.7 and was greatly reduced at other normal force coefficients. Refinements in a 10 percent thick supercritical airfoil ( airfoil 31) have produced significant improvements in the drag characteristics compared with those for an earlier supercritical airfoil ( airfoil 12) designed for the same normal force coefficient of 0.7. Transonic aerodynamic characteristics of the 10-percent- thick NASA supercritical airfoil 31 Some of the airfoil design guidelines are discussed, and coordinates of a matrix of family related supercritical airfoils ranging from thicknesses of 2 to 18 percent and over a design lift coefficient range from 0 to 1.0 are presented. The NASA supercritical airfoil development program is summarized in a chronological fashion. ![]() NASA supercritical airfoils: A matrix of family-related airfoils
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