Chordwise pressure distributions on a 12-foot-span wing of NACA 66-series airfoil sections up to a mach number of 0.60

Nancy E. Wall
Oct 1948

Chordwise pressure distributions are presented from experimental data obtained at six spanwise stations of 12-foot-span wing incorporating NACA 66-series sections. The data shown were obtained at Mach numbers ranging from 0.20 to 0.60 and at angles of attack from -4 degrees to the stalling angle of attack.

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