NACA-TM-X-2317

Abstract

Tests were conducted in the Langley high-speed 7- by 10-food tunnel on a rectangular aspect-ratio-6 wing which had a slotted supercritical airfoil section. The wing was fitted with several high-lift flap systems: plain flap, single-slotted flap, and a double slotted flap, in addition to the slot which exists in this early version of the supercritical airfoil. The plain and single-slotted flaps were 40 percent chord. The double-slotted flap consisted of the 40-percent-chord plain flap with a 15-percent-chord vane. All three flap configurations were tested with a wing leading-edge slat set at various nosedown angles (O° to 60°) with respect to the wing-chord line, Tests were made over an angle-of-attack range of -4° to 20°. The flaps could be set at angles from 30° to 60°, except for the double-slotted flap which was tested up to 70° deflection. Pressure distributions were measured on each segment of the wing and flap at a midsemispan station. The pressure data obtained on this model are believed to represent the two-dimensional data closely since the aspect ratio is relatively large and the wing is rectangular in planform. The results show, as expected, that a leading-edge slat or other device is essential if high-lift capability is to be achieved. The maximum lift coefficient of the flapped system varies from about 2.85 for the plain flap to about 3.65 for the double-slotted flap for flap angles of about 50°with the leading-edge slat at about 40°.