THE EFFECTS OF AN INVERSE-TAPER LEADING-EDGE FLAP ON THE AERODYNAMIC LOADING CHARACTERISTICS OF A 45° SWEPTBACK WING AT MACH NUMBERS TO 0.90

摘要

Measurements have been made of the surface pressures on a plane sweptback wing having an inverse-taper leading-edge flap. Def lection of the flap produced a camber and twist distribution similar to that resulting from incorporation of conical camber in the forward portion of the wing. The wing had-450 of leading-edge sweepback, an aspect ratio of 3, and a taper ratio of 0.4. The results of-tests of the wing-body combination with flap deflections to 16° are presented for a Mach number of 0.25 at a Reynolds number of 15 million and for Mach numbers of 0.60 to 0.90 at a Reynolds number of 3.2 million.nDeflection of the flap decreased the loss in loading near the wing tip which occurred for the plane wing at Mach numbers of 0.60 and greater. However, only small changes in wing normal force and center of pressure accompanied flap deflection. Deflection of the flap increased the maximum flap-section normal force and hinge moment by as much as 100 percent.