Experimental Study of Transonic Flow About a Supercritical Airfoil. Static Pressure and Drag Data Obtained from Tests of a Supercritical Airfoil and an Naca 0012 Airfoil at Transonic Speeds, Supplement

摘要

Surface static-pressure and drag data obtained from tests of two slightly modified versions of the original NASA Whitcomb airfoil and a model of the NACA 0012 airfoil section are presented. Data for the supercritical airfoil were obtained for a free-stream Mach number range of 0.5 to 0.9, and a chord Reynolds number range of 2 x 10 to the 6th power to 4 x 10 to the 6th power. The NACA 0012 airfoil was tested at a constant chord Reynolds number of 2 x 10 to the 6th power and a free-stream Mach number range of 0.6 to 0.8.