# US 11,299,266 B2 · Wing for an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,299,266 B2 - Document ID: US11299266B2 - Status: Granted - Kind: B2 - Application number: 15/793,682 - Filed: 2017-10-25 - Published: 2019-04-25 - Granted: 2022-04-12 - Earliest claimed: 2017-10-25 - Assignees: Gulfstream Aerospace Corporation - Applicants: Gulfstream Aerospace Corporation - Inventors: George Hicks; Donald Howe; Gregory Howe; Joe Gavin - Web page: https://patentgrep.com/patent/US11299266B2 ## CPC - B64C 30/00: Supersonic type aircraft - B64C 3/10: Shape of wings - B64C 23/06: by generating vortices - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge. ## Claims ### Claim 1 A wing for an aircraft, the wing comprising: a wing body having a wingtip, a leading-edge, and a trailing edge, wherein the wingtip comprises an outboard-most portion of the wing body, wherein the leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack, and wherein the trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location inboard of the wingtip and wherein the trailing edge inboard of the aft-most region extends continuously upstream and includes at least one break. ### Claim 2 (depends on 1) The wing of claim 1, wherein the predetermined angle of attack comprises a design condition angle of attack. ### Claim 3 (depends on 2) The wing of claim 2, wherein the design condition angle of attack comprises an angle of attack to be flown by the aircraft during a landing phase of flight. ### Claim 4 (depends on 1) The wing of claim 1, further comprising a wing root disposed along an inboard portion of the wing, wherein the aft-most region is disposed outboard of the wing root. ### Claim 5 A wing for an aircraft, the wing comprising: a wing body having a wingtip, a leading-edge, and a trailing edge, wherein the wingtip comprises an outboard-most portion of the wing, wherein the leading-edge is disposed along a forward portion of the wing body and is configured such that when the aircraft is flown sub-sonically at a first predetermined angle of attack, a vortex will form at the leading-edge and create a low pressure region at a first location on an upper surface of the wing, and when the aircraft is flown sub-sonically at a second predetermined angle of attack greater than the first predetermined angle of attack, the vortex will be repositioned causing the low pressure region to move to a second location on the upper surface of the wing, the second location being aft and inboard of the first location, and wherein the trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip and at a position that corresponds with the second location and wherein the trailing edge inboard of the aft-most region extends continuously upstream and includes at least one break. ### Claim 6 (depends on 5) The wing of claim 5, wherein the leading-edge has a cross-sectional radius and a sweep that cooperate to cause the leading-edge to generate the vortex when the aircraft is flown at the first predetermined angle of attack. ### Claim 7 (depends on 5) The wing of claim 5, wherein the second predetermined angle of attack comprises a design condition angle of attack. ### Claim 8 (depends on 7) The wing of claim 7, wherein the design condition angle of attack comprises an angle of attack to be flown by the aircraft during a landing phase of flight. ### Claim 9 (depends on 5) The wing of claim 5, further comprising a wing root disposed along an inboard portion of the wing, wherein the aft-most region is disposed outboard of the wing root. ### Claim 10 (depends on 5) The wing of claim 5, wherein the aft-most region comprises an aft-most point. ### Claim 11 (depends on 5) The wing of claim 5, wherein the aft-most region is disposed between approximately fifty five percent and approximately eighty five percent of a span of the wing measured in an outboard direction from a root of the wing. ### Claim 12 (depends on 5) The wing of claim 5, wherein a portion of the trailing edge disposed inboard of the wingtip has a curved configuration. ### Claim 13 (depends on 5) The wing of claim 5, wherein the trailing edge has a forward sweep inboard of the aft-most region. ### Claim 14 A wing for an aircraft, the wing comprising: a wing body having a wingtip, a leading-edge, and a trailing edge, wherein the wingtip comprises an outboard-most portion of the wing body; wherein the leading-edge is disposed along a forward portion of the wing body and is configured such that when the aircraft is flown sub-sonically at a first predetermined angle of attack, a vortex will form at the leading-edge, the vortex having a vortex axis extending outboard in a first direction that is substantially aligned with the leading-edge when the aircraft is flown at the first predetermined angle of attack, and the vortex axis extending outboard in a second direction that is oblique with respect to the leading-edge and aft thereof when the aircraft is flown at a second predetermined angle of attack, the second predetermined angle of attack being greater than the first predetermined angle of attack; and wherein the trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip and at a position that corresponds with the vortex axis when the aircraft is flown at the second predetermined angle of attack and wherein the trailing edge inboard of the aft-most region extends continuously upstream and includes at least one break. ### Claim 15 (depends on 14) The wing of claim 14, wherein the second predetermined angle of attack comprises a design condition angle of attack. ### Claim 16 (depends on 14) The wing of claim 14, further comprising a wing root disposed along an inboard portion of the wing, wherein the aft-most region is disposed outboard of the wing root. ### Claim 17 (depends on 14) The wing of claim 14, wherein the aft-most region comprises an aft-most point. ### Claim 18 (depends on 14) The wing of claim 14, wherein the aft-most region is disposed between approximately fifty five percent and approximately eighty five percent of a span of the wing measured in an outboard direction from a root of the wing. ### Claim 19 (depends on 14) The wing of claim 14, wherein a portion of the trailing edge disposed inboard of the wingtip has a curved configuration. ### Claim 20 (depends on 14) The wing of claim 14, wherein the trailing edge has a forward sweep inboard of the aft-most region.