Comparison of the experimental pressure distribution on an NACA 0012 profile at high speeds with that calculated by the relaxation method

James L. Amick
Aug 1950

Pressure-distribution measurements were 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.

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