Highly efficient supersonic laminar flow wing

1. 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.

2. The combination of claim 1 wherein the strake has a leading edge swept more than the Mach angle at maximum supersonic speed of the aircraft.

3. The combination of claim 1 wherein the raked wing tip has

i) more sweep than the Mach angle maximum cruise speed of the supersonic aircraft.

4. The combination of claim 3 wherein said reverse fillet has a convex leading edge profile at said junction.

5. The combination of claim 4 wherein said hybrid plain-split flap is a trailing edge flap and has the following:

i) a plain flap hinge line,

ii) a split flap hinge line located aft of the plain flap hinge line.

6. The combination of claim 1 wherein said reverse fillet has a convex leading edge profile at said junction.

7. The combination of claim 1 wherein said inboard leading edge flap is positioned for deployment;

i) about a pivot axis associated with the strake or fuselage.

8. The combination of claim 1 wherein said hybrid plain-split flap is a trailing edge flap and has the following:

i) a plain flap hinge line,

ii) a split flap hinge line located aft of the plain flap hinge line.

9. The combination of claim 1 wherein said inboard leading edge flap is positioned for deployment from one of the following:

i) a well in the strake or fuselage,

ii) about a pivot axis associated with the strake or fuselage.

10. The combination of claim 1 wherein the plain flap has a hinge line, said split flap has a hinge line, and said hinge lines are co-located.

11. The combination of claim 1 wherein the wing has leading edge sweep of less than about 30°.

12. The combination of claim 1 wherein the strake has leading edge angularity over about 50°.

13. The combination of claim 12 wherein the wing has leading edge sweep of less than about 30°.

14. Improved supersonic laminar flow wing structure, on a supersonic aircraft, having in combination the following:

a) a fuselage,

b) raked wing tip,

c) reversed fillet at fuselage 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 postitioned 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.

15. The combination of claim 14 wherein said reverse fillet has a convex leading edge profile at said junction.