Patent ID: 7946535

Claim:
Improved supersonic laminar flow wing structure, on a supersonic aircraft, having in combination the following: a) strake extending forwardly of the wing inboard extent, b) raked wing tip, c) reversed fillet at strake junction with the wing leading edge, d) there being inboard wing panel span, and including inboard leading edge flap extending over less than about 15% of said inboard wing panel span, e) hybrid plain-split flap associated with the wing and having a lower surface portion deflectable downwardly relative to plain flap extent, said plain flap having a rearward terminal edge, and said split flap extending rearwardly from a forwardmost hinge locus proximate mid-chord of said plain flap, and forward of said terminal edge, f) and wherein the plain flap is positioned to be downwardly deflected at a first angle and the split flap is positioned to be downwardly angled below the plain flap, the plain flap having substantial bodily flatness throughout the majority of its chordal length.