EFFECTS OF LEADING-EDGE SLATS ON THE AERODYNAMIC CHARACTERISTICS OF A 45° SWEEPBACK WING-FUSELAGE CONFIGURATION AT MACH NUMBERS OF 0.4 TO 1.03

摘要

An investigation was conducted in the Langley l6-foot transonic tunnel to determine the aerodynamic characteristics of a wing-fuselage combination with a 45 sweptback wing having NACA 65AOO6 airfoil sec¬tions, an aspect ratio of 4, taper ratio of 0.6, and incorporating out¬board leading-edge slats. Slats of 45 percent semispan and 0°, 10°, and 20° slat deflection, and 35 percent semispan having 0° and 10° deflec¬tion were tested at Mach numbers from OAO to 1.03. For each configura¬tion all or parts of the Mach number-range were investigated through an angle-of-attack range from -2° to 26° at the lowest speeds and from -2°to 8° at the highest speed at Reynolds numbers from 4 x 10° to 6.5 x 10°.