Forward swept winglet
An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.
1. An aircraft, comprising:
a pair of wings;
a forward swept winglet attached proximate to a wing tip of each wing, the forward swept winglet including a leading edge and a trailing edge, the leading edge of each winglet extending from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft; and
at least one mass balance in the winglet forward of the wing's torsional axis.
2. The aircraft of claim 1 , wherein the predetermined forward sweep angle is determined by a group of parameters comprising a weight of the winglet, a wing span and area of each wing, a cruise Mach number of the aircraft, balancing mass in the winglet and reducing induced drag.
3. The aircraft of claim 1 , wherein the forward swept winglet comprises a root chord that is substantially equal in length to the chord of the wing tip.
4. The aircraft of claim 1 , wherein a root chord of the forward swept winglet is shorter than the chord of the wing tip.
5. The aircraft of claim 1 , wherein a root chord of the forward swept winglet is longer than the chord of the wing tip.
6. The aircraft of claim 1 , wherein the forward swept winglet comprises a root that is attached to the wing tip offset a selected distance in either a forward or aft direction relative to the chord of the wing tip.
7. The aircraft of claim 1 , wherein the trailing edge of the forward swept winglet extends from the wing at a selected forward sweep angle relative to the line perpendicular to the chord of the wing tip.
8. The aircraft of claim 7 , wherein the selected forward sweep angle of the trailing edge of the winglet is greater than the predetermined forward sweep angle of the leading edge of the winglet.
9. The aircraft of claim 1 , wherein the forward swept winglet extends above the wing.
10. The aircraft of claim 1 , wherein the forward swept winglet comprises a lower forward swept winglet portion extending below the wing.
11. The aircraft of claim 1 , wherein the forward swept winglet comprises:
an upper winglet portion extending above the wing at the predetermined forward sweep angle; and
a lower portion extending below the wing.
12. The aircraft of claim 11 , wherein the at least one mass balance comprises at least one mass balance of a chosen weight positioned at a selected location in at least one of the upper winglet portion and the lower winglet portion.
13. The aircraft of claim 11 , wherein the at least one mass balance comprises a mass balance of a chosen weight positioned at a farthest forward position of each of the upper winglet portion and the lower winglet portion.
14. The aircraft of claim 1 , wherein the forward swept winglet extends from the wing at a chosen angle in a direction inboard toward the fuselage or outboard away from the fuselage, the chosen angle being between substantially vertical to an extent of the wing and about 45 degrees from substantially vertical.
15. The aircraft of claim 1 , wherein the aircraft comprises one of an elongated fuselage to which the wings are attached, a blended wing body configuration and a flying wing configuration wherein the pair of wings are joined to form a single wing structure.
16. An aircraft, comprising:
a wing;
a forward swept winglet attached proximate to a wing tip of the wing, the forward swept winglet comprising an upper winglet portion extending above the wing and a lower winglet portion extending below the wing, a leading edge of at least the upper winglet portion extending from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft; and
at least one mass balance in the winglet forward of the wing's torsional axis.
17. The aircraft of claim 16 , wherein the lower winglet portion includes a leading edge and a trailing edge, the leading edge of the lower winglet portion extending from the wing at a selected forward sweep angle relative to the line perpendicular to the chord of the wing tip in a direction toward the forward portion of the aircraft.
18. The aircraft of claim 16 , wherein the at least one mass balance comprises a mass balance of a chosen weight positioned at a farthest forward position of each of the upper winglet portion and the lower winglet portion.
19. A method to reduce wing flutter in an aircraft wing designed to provide a substantially increased lift-to-drag ratio, the method comprising:
attaching a forward swept winglet proximate to a wing tip of each wing of the aircraft, the forward swept winglet including a leading edge and a trailing edge, the leading edge of each winglet extending at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft; and
providing at least one mass balance in the winglet forward of the wing's torsional axis.
20. The method of claim 19 , wherein attaching the forward swept winglet comprises:
attaching an upper winglet portion extending above the wing at the predetermined forward sweep angle; and
attaching a lower winglet portion extending below the wing.