Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections

Stanley F. Racisz
naca-tn-2824
Nov 1952


An investigation has been made in the Langley low-turbulence pressure tunnel to determine the effects of Mach number and Reynolds number on the maximum-lift characteristics of the NACA 65-006, 64-009, 64-210, and 64(2)-215 airfoil sections in the smooth condition and in the conditions with leading-edge roughness.

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http://naca.central.cranfield.ac.uk/reports/1952/naca-tn-2824.pdf