INVESTIGATION OF THE EFFECTS OF LEADING-EDGE FLAPS ON THE AERODYNAMIC CHARACTERISTICS IN PITCH AT MACH NUMBERS FROM 0.40 TO 0.93 OF A WING-FUSELAGEnCONFIGURATION WITH A 45° SWEPTB ACK WING OF ASPECT RATIO 4

摘要

An investigation was made to determine the effects of a number of leading-edge flaps on the aerodynamic characteristics in pitch of a wing-fuselage configuration with a 45° sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65AOO6 airfoil section. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0A0 to 0.93 and an angle-of-attack range of about -2° to 24°. Lift, drag, and pitching-moment data were obtained for all configurations.nAll the leading-edge flaps investigated reduced the drag in the medium lift range. Full-span and outboard partial-span, flaps deflected 3° or 6° usually gave better maximum lift-drag ratios than any of the other leading-edge flap arrangements investigated throughout the Mach number range. In general, all leading-edge flaps delayed the sharp pitch-up tendencies of this model by from 0.2 to O.4 lift coefficient up to a Mach number of 0.90, but provided little or no improvement at the highest Mach numbers investigated.