Laminar flow wing optimized for transonic cruise aircraft
View Patent ↗On an aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, and (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip.
1. An aircraft having maximum efficient cruise speed in a range from about Mach 0.8 to about Mach 1.2, and having a fuselage and wings with:
(a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along a wing semi-span outboard from a zone of substantial fuselage influence, and
(b) a wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to a wing tip.
2. The aircraft of claim 1 including fuselage lengthwise contours to minimize or reduce a wave drag of a combined wing and fuselage, including engine nacelles and empennage and other lifting and control surfaces.
3. The aircraft of claim 2 having fuselage and wing contours, including airfoil and sweep, to minimize or reduce total drag of the combined wing-fuselage, including effects of laminar flow in reducing skin friction drag.
4. The aircraft of claim 3 having empennage contours to minimize or reduce total drag of a combined wing, fuselage and empennage.
5. The aircraft of claim 4 having wing and empennage contours to maximize or increase a total range of the aircraft for a given maximum total takeoff weight or other related constraint, including the effects of thickness-to-chord ratio and sweep on a structural weight of the wings and empennage.
6. The aircraft of claim 4 having wing and empennage contours to minimize or decrease a total weight of the aircraft for a given mission or mix of missions, including effects of thickness-to-chord ratio and sweep on a structural weight of the wings and empennage.
7. The aircraft of claim 4 having wing and empennage contours to minimize or decrease a total weight of the aircraft for a given anticipated flight mission or mix of missions, including effects of thickness-to-chord ratio and sweep on a structural weight of the wings and empennage, where such wing and empennage contours are characterized by either (a) an iterative process combining configuration design experience, aerodynamic analysis and wind tunnel testing, or (b) a computer-based multi-disciplinary optimization method combined with configuration design constraints.
8. The aircraft of claim 1 wherein a drag rise Mach number lies between about 0.80 and 0.97.
9. The aircraft of claim 1 wherein a drag rise Mach number lies between about 0.97 and 1.2.
10. The aircraft of claim 1 wherein a drag rise Mach number lies between about 0.92 and 0.97, for a wing average t/c of about 3%.
11. The aircraft of claim 1 wherein a drag rise Mach number lies between about 0.95 and 1.15, for a wing average t/c of about 3%.
12. The aircraft of claim 1 having about 3% average wing t/c, characterized in that Mdd, corresponding to about 0.002 drag coefficient increase, occurs at about Mach 0.96.
13. The aircraft of claim 1 having about 3% average wing t/c, characterized in that wing leading edge sweep is between about 20 degrees and about 35 degrees, and by a supersonic drag rise Mach number between about 0.99 and 1.05.
14. The aircraft of claim 1 having wing leading edge sweep less than about 25 degrees, characterized in that wing average t/c is between about 3% and 8%.
15. The aircraft of claim 1 having wing leading edge sweep between about 20 degrees and 35 degrees, characterized in that wing average t/c is less than about 3%.