# US 11,299,255 B2 · Aircraft slat including angled outboard edge > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,299,255 B2 - Document ID: US11299255B2 - Status: Granted - Kind: B2 - Application number: 16/468,235 - Filed: 2017-11-16 - Published: 2020-03-05 - Granted: 2022-04-12 - Earliest claimed: 2016-12-12 - Assignees: Bombardier Inc. - Applicants: Bombardier Inc. - Inventors: Fassi Kafyeke; Marc Langlois - Web page: https://patentgrep.com/patent/US11299255B2 ## CPC - B64C 9/24: by single flap - B64C 23/06: by generating vortices - B64C 23/069: {using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips} - B64C 9/22: at the front of the wing - Y02T 50/10: Drag reduction - Y02T 50/30: Wing lift efficiency - Y02T 50/40: Weight reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A slat (50) for an aircraft wing comprises a leading edge (51) defining a leading edge line (61), a trailing edge (52) defining a trailing edge line (62), the leading and trailing edges line defining a slat plane, the chord distance (69) extending normal to the leading edge and measured along the slat plane; an inboard edge extending between the leading and trailing edges; and an outboard edge (56) extending between the leading and trailing edges. The outboard edge comprises a first side portion having a projection on the plane defining a first side line (63), and a second side portion having a projection on the plane defining a second side line (64), the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line as it extends toward the inboard and trailing edges. A wing assembly and an aircraft including the slat are also disclosed. ## Claims ### Claim 1 A slat for an aircraft wing, comprising: a leading edge defining a leading edge line connecting forward-most points of the slat and extending between an inboard end and an outboard end; a trailing edge defining a trailing edge line connecting aft-most points of the slat, extending between the inboard end and the outboard end, and being disposed a chord distance from the leading edge in a hingewise direction, the leading edge line and the trailing edge line defining a slat plane, the chord distance between the leading edge and the trailing edge extending normal to the leading edge, the chord distance being measured along the slat plane; an inboard edge extending from the leading edge to the trailing edge; and an outboard edge extending from the leading edge to the trailing edge, the outboard edge comprising: a first side portion extending from the leading edge to an intermediate point between the leading edge and the trailing edge, a projection of the first side portion onto the slat plane defining a first side line, and a second side portion extending from the intermediate point to the trailing edge, a projection of the second side portion onto the slat plane defining a second side line, the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line, the second side line extending toward the inboard edge as it extends toward the trailing edge, a slat vortex created by air flowing over the outboard edge of the slat being directed toward an inboard side of the wing when the wing is connected to an airplane. ### Claim 2 (depends on 1) The slat according to claim 1, wherein the first side line is a straight line. ### Claim 3 (depends on 1) The slat according to claim 1, wherein the second side line is a straight line. ### Claim 4 (depends on 1) The slat according to claim 1, wherein the first side line extends for 60% or less of the chord distance. ### Claim 5 (depends on 1) The slat according to claim 1, wherein the first side line extends for at least 40% of the chord distance. ### Claim 6 (depends on 1) The slat according to claim 1, wherein: the first side line is perpendicular to the leading edge line; and the first angle and the second angle are complementary angles. ### Claim 7 (depends on 1) The slat according to claim 1, wherein the second angle is at least 45 degrees. ### Claim 8 (depends on 1) The slat according to claim 1, wherein the second angle is less than 45 degrees. ### Claim 9 (depends on 1) The slat according to claim 1, wherein a projection of the inboard edge onto the slat plane is parallel to the line extending normal to the leading edge. ### Claim 10 (depends on 1) The slat according to claim 1, wherein the slat is an outboard-most slat of the aircraft wing. ### Claim 11 (depends on 1) The slat according to claim 1, wherein the first side portion and the second side portion of the outboard edge provide at least one of a lift coefficient CL and a pitch moment coefficient CM that change with respect to an angle of attack of the aircraft. ### Claim 12 A wing assembly comprising: a wing body; a winglet connected to a tip of the wing body; and a slat movably connected to the wing body, the slat comprising: a leading edge defining a leading edge line connecting forward-most points of the slat and extending between an inboard end and an outboard end; a trailing edge defining a trailing edge line connecting aft-most points of the slat, extending between the inboard end and the outboard end, and being disposed a chord distance from the leading edge in a hingewise direction, the leading edge line and the trailing edge line defining a slat plane, the chord distance between the leading edge and the trailing edge extending normal to the leading edge, the chord distance being measured along the slat plane; an inboard edge extending from the leading edge to the trailing edge; and an outboard edge extending from the leading edge to the trailing edge, the outboard edge comprising: a first side portion extending from the leading edge to an intermediate point between the leading edge and the trailing edge, a projection of the first side portion onto the slat plane defining a first side line, and a second side portion extending from the intermediate point to the trailing edge, a projection of the second side portion onto the slat plane defining a second side line, the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line, the second side line extending toward the inboard edge as it extends toward the trailing edge, a slat vortex created by air flowing over the outboard edge of the slat being directed toward an inboard side of the wing assembly when the wing assembly is connected to an airplane. ### Claim 13 (depends on 12) The wing assembly according to claim 12, wherein the first side line is a straight line. ### Claim 14 (depends on 12) The wing assembly according to claim 12, wherein the second side line is a straight line. ### Claim 15 (depends on 12) The wing assembly according to claim 12, wherein the first side line extends for 60% or less of the chord distance. ### Claim 16 (depends on 12) The wing assembly according to claim 12, wherein the first side line extends for at least 40% of the chord distance. ### Claim 17 (depends on 12) The wing assembly according to claim 12, wherein: the first side line is perpendicular to the leading edge line; and the first angle and the second angle are complementary angles. ### Claim 18 (depends on 12) The wing assembly according to claim 12, wherein the second angle is at least 45 degrees. ### Claim 19 (depends on 12) The wing assembly according to claim 12, wherein the second angle is less than 45 degrees. ### Claim 20 (depends on 12) The wing assembly according to claim 12, wherein a projection of the inboard edge onto the slat plane is parallel to the line extending normal to the leading edge. ### Claim 21 (depends on 12) An airplane comprising: a fuselage; and two oppositely disposed wing assemblies, according to claim 12, connected to the fuselage.