PURPOSE: To provide vortex drag reduction effect which is equal to that obtained when a wing end is extended, reduce induced drag, and increase lift/ drag ratio without extending an end of a wing which is thin and long vertically and unique to a supersonic aircraft. CONSTITUTION: In a main wing of a supersonic aircraft which flies at Mach number of 1-5, a winglet is mounted in non-plane manner by making a rear fringe coincide with a wing end section of the main wing, and the plane shape of the winglet is trapezoidal type having low aspect ratio. The winglet having front fringe retraction angle LE is formed in such a way that LE. winglet=MCOS-1 (1/M), and cant angle is in a scope of 90=70 deg.. Furthermore, mounting angle is 0-1 deg., chord length Cr.w of a wing root section of the winglet is in a scope of Ct=Cr.w=Ct/2 in which it is smaller than chord length Ct of the wing end section of the main wing and larger than a half of the chord length Ct, and the ratio of the chord length Cr.w of the wing root section of the winglet to the chord length Ct.w of the wing end is in a scope of 0.5==0.2 so that the main wing of the supersonic aircraft has the shape in which torsion distribution is not provided in the winglet.
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