AN INVESTIGATION AT TRANSONIC SPEEDS OF THE EFFECTS OF FENCES, DROOPED NOSE, AND VORTEX GENERATORS ON THE AERODYNAMIC CHARACTERISTICS OF A WING-FUSELAGE COMBINATION HAVING A 6-PERCENT-THICK, 45° SWEPTB.ACK WING

摘要

An investigation has been made at transonic speeds to determine the effects of fences drooped nose, combination fences and drooped nose, and vortex generators on the aerodynamic characteristics of a 45 sweptback wing-fuselage configuration. The wing has an aspect ratio of 4, a taper ratio of 0.6, NACA 65A006 airfoil sections parallel to the plane of symmetry, and no geometric twist, dihedral, or incidence The tests were conducted in the Langley l6-foot transonic tunnel at Mach numbers from 0.60 to 1.03.nThe results show that the fences increased the lift coefficient at which adverse pitching-moment changes occurred in the Mach number range from 0.60 to about 0.90 and at Mach numbers above 0.98. Drooping the forward 14 percent of the airfoil 3° from the 0.65-semispan stations to the tip increased the lift coefficient at which undesirable pitching-moment changes occurred at Mach numbers of O.98 and 1.00. A combina¬tion of the fences and drooped nose improved the pitching-moment characteristics at all Mach numbers where beneficial effects were realized from either of the individual configurations. The drooped-nose configuration was more effective than the fences in increasing the lift-drag ratio. The vortex generators installed at the wing leading edge or at the 0.15 chordwise station resulted in no significant improvement in the pitching-moment characteristics.