Effects of Mach number variation between 0.07 and 0.34 and Reynolds number variation between 0.97 x 10(exp 6) and 8.10 x 10(exp 6) power on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections

James E. Fitzpatrick, WIlliam C. Schneider
naca-tn-2753
Aug 1952


The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and 0.08 to 0.26 at a pressure of 3 pounds per square inch absolute.

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