Highly efficient supersonic laminar flow wing structure

1. Improved supersonic laminar flow wing structure, on a supersonic aircraft, the wing structure characterized as forwardly sharp, and thin along its chordal extent, and having in combination the following:

a) a fuselage,

b) reversed fillet at fuselage junction with the wing leading edge, said reversed fillet having a forward edge defining a first edge portion angled forwardly toward the fuselage and a second edge portion angled rearwardly toward the fuselage.

2. Improved supersonic laminar flow wing structure as defined in claim 1 wherein said reversed fillet has a convex leading edge profile at said junction between said two edge portions.

3. Improved high speed laminar flow wing structure, on an aircraft, having in combination the following:

a) strake extending forwardly of the wing inboard extent,

b) wing reversed fillet at strake junction with the wing leading edge,

c) said strake having a highly swept, blunt leading edge, and providing fuel receiving space,

d) said reversed fillet itself having a leading edge which is convex at a fillet junction with said strake,

e) said reverse fillet leading edge defining a first edge portion angled forwardly toward the fuselage, and a second edge portion angled rearwardly toward the fuselage.

4. The combination of claim 3 wherein the wing has leading edge sweep of less than about 30°.

5. Improved high speed laminar flow wing structure, on an aircraft, having in combination the following:

a) a wing reversed fillet at junction with the inboard end of wing leading edge,

b) said reversed fillet itself having a leading edge which is convex at a fillet junction with said fuselage,

c) said reversed fillet leading edge defining a first edge portion which is angled forwardly toward the fuselage, and a second edge portion angled rearwardly toward the fuselage.