EFFECT OF LEADING-EDGE CHORD-EXTENSIONS ON THE AERODYNAMIC-CHARACTERISTICS OF A 450 SWEPTBACK WING-FUSELAGE COMBINATION AT MACH NUMBERS OF 0.40 TO 1.03

摘要

An investigation has been conducted in the Langley l6-foot transonic tunnel to determine the effect of leading-edge chord-extensions on the aerodynamic characteristics of a sweptback wing-fuselage combination at Mach numbers of 0.40 to 1.03. The wing had 45 sweep, aspect ratio of 4, taper ratio of 0.6, and NACA 65A006 airfoil sections. The investigation included chord-extensions that covered from 55, 65, or 70 percent of the wing semispan to almost the wing tip. They extended chordwise either 15 or 20 percent of the local basic-wing chord.