Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method

Abstract

Note presenting pressure-distribution measurements made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4- by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method.