EXPERIMENTAL INVESTIGATION AT HIGH SUBSONIC SPEEDS OF THE EFFECTS OF LEADING-EDGE RADIUS ON THE AERODYNAMIC CHARACTERISTICS OF A SWEPTBACK-WING— FUSELAGE COMBINATION WITH LEADING-EDGE FLAPS AND CHORD-EXTENSIONS

摘要

A limited investigation was made at high subsonic speeds to deter-mine the effects of wing leading-edge radius on the aerodynamic charac-teristics of a sweptback-wing—fuselage combination with leading-edge flaps and chord-extensions. The basic wing had 45° sweepback, aspect ratio 4, taper ratio 0.3, and NACA 65AOO6 airfoil section. The leading-edge shapes considered consisted of a sharp leading edge, a normal air¬foil leading edge, and a leading edge formed by using three times the normal radius and fairing the new nose contour smoothly into the normal airfoil. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.80 to O.92 and an angle-of-attack range of -2° to 24°. lift drag, and pitching-moment data were obtained for all configurations with leading-edge flap deflections of 0° and 6°.