Pressure Distributions From Subsonic Tests of a NACA 0012 Semispan Wing Model

An unswept, semispan wing model incorporating a NACA 0012 airfoil section was tested in the Langley 14- by 22-Foot Subsonic Tunnel. This report contains pressure data which document effects of wing configuration and free-stream conditions on wing pressure distribution. The untwisted wing incorporated a full-span, leading-edge Krueger flap and a full-span, single-slotted trailing-edge flap. Three wing configurations were tested: cruise, trailing-edge flap only, and high-lift (Krueger flap and trailing-edge flap deployed). The trailing-edge flap was tested at a deflection angle of 40 degrees and the Krueger flap at a deflection of 55 degrees. Tests were conducted at free-stream dynamic pressures of 15, 30 and 60 psf, with corresponding chord Reynolds numbers of 1.22 x 10 super 6 to 2.11 x 10 super 6, and Mach numbers of 0.12 to 0.20. Angles of attack presented range from 0 to 20, depending on the wing configuration. The data are presented without analysis.