Fairings for wing-mounted engines

Abstract

To provide fairings to support engines relative to wings of an aircraft, and methods for reducing drag.SOLUTION: A wing comprises a fairing 130 covering a pylon to connect to an engine. The fairing defines a horizontal plane, a first plane perpendicular to a longitudinal axis, and a second plane perpendicular to the longitudinal axis and aft of the first plane. A reference line is defined as the longitudinal axis when projected onto the horizontal plane. The fairing includes a fairing body defining an aerodynamic surface. The aerodynamic surface has an outboard portion and an inboard portion. The inboard portion is configured such that the first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection point. The first intersection point is laterally displaced from the reference line by a first distance. The second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection point. The second intersection point is laterally displaced from the reference line by a second distance, which is greater than the first distance.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] This disclosure broadly relates to aerospace structures, and more particularly to fairings and methods for reducing drag on aircraft. [Background technology]

[0002] Aircraft with engines mounted on the wings typically utilize support structures, such as pylons, to support the engines relative to the wings. Many aircraft experience significant drag and interference near the engine-pylon junction, thus posing a risk of damage or adverse effects to the aircraft. Current solutions to reduce drag and interference include relocating the engines, slowing the aircraft's speed, or altering the wing's shape and dimensions. These solutions are not ideal because they increase weight, lengthen flight times, and make it impossible to modify the wing shape for different aircraft configurations.

[0003] Therefore, those skilled in the art continue their research and development efforts in the field of improving structures and methods for reducing drag on aircraft. [Overview of the Initiative]

[0004] The following is a non-exclusive list of embodiments of the subject matter of this disclosure, which may or may not be claimed.

[0005] A fairing for an aircraft is disclosed. The aircraft includes a wing that defines a longitudinal axis and has a leading edge, a trailing edge behind the leading edge, a wing thickness, and a chord. The aircraft further includes an engine having a longitudinal axis perpendicular to the chord and parallel to the longitudinal axis of the aircraft. The aircraft further includes pylons connecting the wing to the engine. The fairing covers and supports the pylons. The fairing defines a horizontal plane, a first plane perpendicular to the longitudinal axis, and a second plane perpendicular to the longitudinal axis and behind the first plane. The longitudinal axis defines a reference line when projected onto a horizontal plane.

[0006] As one embodiment, the disclosed fairing includes a fairing body that defines an aerodynamic surface. The aerodynamic surface includes an outboard portion and an inboard portion. The inboard portion is configured such that a first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection. The first intersection is shifted laterally by a first distance from a reference line. A second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection. The second intersection is shifted laterally by a second distance from a reference line. The second distance is longer than the first distance.

[0007] Methods for reducing drag on the aircraft are also disclosed. The aircraft includes a main wing that defines a longitudinal axis and has a leading edge, a trailing edge behind the leading edge, a wing thickness, and a chord. The aircraft further includes an engine having a longitudinal axis aligned vertically with the chord and a longitudinal axis parallel to the longitudinal axis of the aircraft. The aircraft further includes pylons connecting the main wing to the engine. The aircraft further includes a fairing. The fairing defines a horizontal plane, a first plane perpendicular to the longitudinal axis, and a second plane perpendicular to the longitudinal axis and behind the first plane. The longitudinal axis defines a reference line when projected onto a horizontal plane.

[0008] As one embodiment, the method includes arranging a fairing to cover a pylon. The fairing includes a fairing body that defines an aerodynamic surface. The aerodynamic surface includes an outboard portion and an inboard portion. The inboard portion is configured such that a first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection. The first intersection is shifted laterally by a first distance from a reference line. A second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection. The second intersection is shifted laterally by a second distance from a reference line. The second distance is longer than the first distance.

[0009] Other embodiments of the fairing and method disclosed will become clear from the following detailed description, the accompanying drawings, and the accompanying claims. [Brief explanation of the drawing]

[0010] [Figure 1] This is a schematic top cross-sectional view of a portion of an aircraft. [Figure 2] Figure 1 is a schematic side perspective view of a portion of the aircraft. [Figure 3] This is a schematic diagram of a plane projected from the intersection of a portion of the aircraft shown in Figure 1. [Figure 4] Figure 1 is a schematic cross-sectional view of a portion of the main wing of an aircraft. [Figure 5] This is a flowchart illustrating methods for reducing drag on an aircraft. [Figure 6] This is a flowchart illustrating aircraft manufacturing and maintenance procedures. [Figure 7] This is a schematic block diagram of one embodiment of an aircraft. [Modes for carrying out the invention]

[0011] Modes for carrying out the following inventions are referenced in the accompanying drawings, which illustrate specific examples described herein. Other embodiments having various structures and functions do not depart from the scope of this disclosure. Similar reference numerals may represent the same features, elements, or components in different drawings.

[0012] Exemplary and non-exclusive examples of the subject matter of this disclosure, which may or may not be patentable, are provided below. Where the “Example” is used herein, it means that one or more features, structures, elements, components, properties, and / or operating steps described in relation to such example are included in at least one aspect, embodiment, and / or embodiment of the subject matter relating to this disclosure. Thus, throughout this disclosure, expressions such as “an example,” “another example,” and similar phrases may, but not necessarily, refer to the same example. Furthermore, the subject matter characterizing any one example may, but not necessarily, include the subject matter characterizing any of the other examples. Furthermore, the subject matter characterizing any one example may, but not necessarily, be combined with the subject matter characterizing any of the other examples.

[0013] Referring to Figure 1, a fairing 130 for aircraft 100 is disclosed. The fairing 130 is configured to reduce the effects of interference between the engine 130 and the airframe at high speeds, such as around Mach 0.70 or higher. Design considerations for the fairing 130 include a torque box and a shield. The shape and dimensions of the disclosed fairing 130 are such that the longitudinal axis A of the engine 110 is located near the underside of the main wing 120 for more than the first approximately one-third of the chord, in order to reduce and eliminate the cruising shock waves generated by the engine 110. LIt may be angled outward. The disclosed fairing 130 is further configured to reduce the growth of drag rise at elevated Mach numbers, such as Mach about 0.70 or greater. Further, the disclosed fairing 130 is configured to reduce the promotion of boundary layer separation induced by shock waves and potential damage loads to the aircraft 100. The disclosed fairing 130 may be ideal for smaller aircraft 100 having rigid and / or thin wings, such as single-aisle aircraft.

[0014] Still referring to FIGS. 1 and 7, the aircraft 100 defines a longitudinal central axis A and includes a main wing 120 having a leading edge 122, a trailing edge 124 behind the leading edge 122, a main wing thickness T W , and a wing chord 126. The aircraft 100 further includes an engine 110. The aircraft 100 further includes a pylon 140 that connects the main wing 120 to the engine 110.

[0015] The engine 110 has a longitudinal axis A L (FIGS. 1 and 2) that is parallel to the longitudinal central axis A of the aircraft 100 and defines the longitudinal axis A L . The engine 110 further defines a central axis A C as shown in FIG. 2. In one embodiment, the central axis A C is aligned with the longitudinal axis A L . In another embodiment, the central axis A C is offset from the longitudinal axis A L by between about 1 degree and about 10 degrees, such as when the engine 110 is mounted slightly inwardly (or outwardly) with respect to the longitudinal central axis A of the aircraft 100.

[0016] In one or more embodiments, the fairing 130 is supported covering the pylon 140. The fairing 130 defines a horizontal plane P H , a first plane P1 perpendicular to the longitudinal axis A L , and a second plane P2 perpendicular to the longitudinal axis A L (see FIG. 2). The horizontal plane P HThe fairing 130 may be cut in half. Similarly, the first plane P1 and the second plane P2 may cut the fairing 130 in half. The second plane P2 is located behind the first plane P1. The longitudinal axis A of the engine 110 L is the horizontal plane P H When projected onto the baseline L, R This defines (see Figure 3).

[0017] Still referring to Figure 1, in one or more embodiments, the fairing 130 includes a fairing body 136 defining an aerodynamic surface 136'. The aerodynamic surface 136' is a single monolithic piece defining an outboard portion 132 and an inboard portion 134. In one or more embodiments, the inboard portion 134 of the aerodynamic surface 136' has different shape and dimensions from the outboard portion 132 of the aerodynamic surface 136'.

[0018] The inboard portion 134 is such that the first plane P1 is horizontal at the first intersection I1 H It is configured to intersect with the aerodynamic surface 136' of the inboard portion 134 of the fairing body 136. The first intersection I1 is located on the reference line L R It is shifted laterally by a distance D1 from the first point.

[0019] The second plane P2 is parallel to the horizontal plane P at the second intersection I2. H The second intersection point I2 intersects with the reference line L R It is shifted laterally by a second distance D2. In one embodiment, the second distance D2 is longer than the first distance D1.

[0020] Referring to Figure 3, in one or more embodiments, the first intersection I1 and the second intersection I2 define line S. Line S is at an angle θ of approximately 1 to 10 degrees relative to the reference line L. R It intersects with the reference line L at an angle θ of about 2 to about 7 degrees. In another embodiment, line S intersects with the reference line L. R It intersects with the reference line L at an angle θ of approximately 3 to 6 degrees. In yet another embodiment, line S intersects with the reference line L R It intersects with it.

[0021] Referring to Figure 3, in one or more embodiments, the chord 126 is on the horizontal plane P H The reference segment C is defined when projected onto the wing. The reference segment C is the leading edge C adjacent to the leading edge 122 of the main wing 120. L The reference segment C is the trailing edge C adjacent to the trailing edge 124 of the main wing 120. A , and front end C L From the rear end C A Length C W It has. In one embodiment, the first plane P1 has a length C of the reference segment C. W It intersects with the reference segment C at a point located approximately 5% to 15% along the line. In another embodiment, the first plane P1 is located along the length C of the reference segment C. W It intersects with the reference segment C at a point located approximately 10% along the line. Furthermore, in one or more embodiments, the second plane P2 is along the length C of the reference segment C. W It intersects the reference segment C at a point located approximately 20% to 40% along the line. In another embodiment, the second plane P2 is along the length C of the reference segment C. W It intersects with the reference segment C at a point located approximately 30% along the line.

[0022] Referring to Figure 4, in one or more embodiments, the horizontal plane P H However, from the lowest point of the wing surface at 128 degrees to the vertical axis A V It is shifted vertically along the horizontal plane P. H The main wing thickness T W The distance is a function of the vertical axis A, from the lowest point of the wing surface (128) to the vertical axis A. V It may be offset vertically along the horizontal plane P. In one embodiment, the horizontal plane P H However, the wing thickness T W At least 0.5 times the distance from the lowest point of the wing surface (128) to the vertical axis A V It may be offset vertically along the vertical axis A. V is the horizontal plane P H It is perpendicular to the horizontal plane P. In another embodiment, the horizontal plane P H However, the wing thickness T WAt least 1x the distance from the lowest point of the wing surface 128 to the vertical axis A V It is shifted vertically along the vertical axis A. V is the horizontal plane P H It is perpendicular to the horizontal plane P. In yet another embodiment, the horizontal plane P H However, the wing thickness T W At least 1.5 times the distance from the lowest point of the wing surface (128) to the vertical axis A V It is shifted vertically along the vertical axis A. V is the horizontal plane P H It is perpendicular to the horizontal plane P. Furthermore, in one or more embodiments, the horizontal plane P H However, the wing thickness T W At least twice that distance, from the lowest point of the wing surface 128 to the vertical axis A V It may be offset vertically along the vertical axis A. V is the horizontal plane P H It is perpendicular to it.

[0023] Referring to Figure 3, in one or more embodiments, the outboard portion 132 of the fairing 130 is such that the first plane P1 is horizontal at the third intersection I3. H and is configured to intersect with the aerodynamic surface 136' of the outboard portion 132. The third intersection I3 is on the reference line L R It is shifted laterally by a third distance D3 from that point.

[0024] In one or more embodiments, the second plane P2 is aligned with the horizontal plane P at the fourth intersection I4. H and intersects with the aerodynamic surface 136' of the outboard portion 132. The fourth intersection I4 is on the reference line L R It is shifted laterally by a fourth distance D4. In one embodiment, the third distance D3 is longer than the fourth distance D4.

[0025] Also disclosed are aircraft having a fairing 130 as shown and described herein.

[0026] Referring to Figure 5, a method 200 for reducing drag on an aircraft 100 is disclosed. The aircraft 100 has a longitudinal central axis A. The aircraft 100 has a main wing 120, with a leading edge 122, a trailing edge 124 behind the leading edge 122, and a wing thickness T W , and a main wing 120 having a chord 126. The aircraft 100 has a longitudinal axis A aligned vertically with respect to the chord 126. L and the longitudinal axis A is parallel to the longitudinal axis A of the aircraft. L The engine 110 further includes an engine 110 having a central axis A C Further definitions are provided. In one embodiment, the central axis A C However, the longitudinal axis A L It is parallel to or overlaps with the central axis A. In another embodiment, the central axis A C However, the longitudinal axis A L It is offset by approximately 1 to 10 degrees.

[0027] The aircraft 100 further includes a pylon 140 connecting the main wing 120 to the engine 110, and a fairing 130 configured to cover and support the pylon 140. The fairing 130 is located on a horizontal plane P H Long axis A L A first plane P1 perpendicular to the longitudinal axis A L Define a second plane P2 perpendicular to the first plane P1. The second plane P2 lies behind the first plane P1. Longitudinal axis A L is the horizontal plane P H When projected onto the baseline L, R This defines...

[0028] Referring to Figure 5, in one or more embodiments, method 200 includes positioning the fairing 130 over the pylon 140 210. Referring to Figure 1, in one or more embodiments, the fairing 130 includes a fairing body 136 defining an aerodynamic surface 136'. The aerodynamic surface 136' is a single monolithic piece defining an outboard portion 132 and an inboard portion 134. In one or more embodiments, the inboard portion 134 of the aerodynamic surface 136' has different shape dimensions from the outboard portion 132 of the aerodynamic surface 136'.

[0029] The inboard portion 134 is configured to be angled away from the longitudinal axis A of the engine 110. In one or more embodiments, the inboard portion 134 is such that a first plane P1 intersects the horizontal plane P at a first intersection point I1 L and the aerodynamic surface 136' of the inboard portion 134. The first intersection point I1 is offset laterally from the reference line L H by a first distance D1. R

[0030] A second plane P2 intersects the horizontal plane P at a second intersection point I2 H and the aerodynamic surface 136' of the inboard portion 134. The second intersection point I2 is offset laterally from the reference line L R by a second distance D2. In one embodiment, the second distance D2 is longer than the first distance D1.

[0031] Referring to FIG. 3, in one or more embodiments, the first intersection point I1 and the second intersection point I2 define a line S. The line S intersects the reference line L at an angle θ of from about 1 degree to about 10 degrees R In another embodiment, the line S intersects the reference line L at an angle θ of from about 2 degrees to about 7 degrees R In yet another embodiment, the line S intersects the reference line L at an angle θ of from about 3 degrees to about 6 degrees R

[0032] Referring to FIG. 3, in one or more embodiments, the chord 126 defines a reference segment C when projected onto the horizontal plane P H The reference segment C has a leading end C L , a trailing end C A , and a length C from the leading end C L to the trailing end C A In one embodiment, the first plane P1 intersects the reference segment C at a point positioned along the length C of the reference segment C at from about 5% to about 15%. In another embodiment, the first plane P1 intersects the reference segment C at a point positioned along the length C of the reference segment C W W WIt intersects the reference segment C at a point positioned approximately 10% along. Further, in one or more embodiments, the second plane P2 intersects the reference segment C at a point positioned approximately 20% to approximately 40% along the length C of the reference segment C W In another embodiment, the second plane P2 intersects the reference segment C at a point positioned approximately 30% along the length C of the reference segment C W It intersects the reference segment C at a point positioned approximately 30% along.

[0033] Referring to FIG. 4, in one or more embodiments, the horizontal plane P H is displaced vertically along the vertical axis A W by at least 0.5 times the distance of the main wing thickness T from the lowest point 128 of the main wing surface V The vertical axis A V is perpendicular to the horizontal plane P H In another embodiment, the horizontal plane P H is displaced vertically along the vertical axis A W by at least 1 times the distance of the main wing thickness T from the lowest point 128 of the main wing surface V The vertical axis A V is perpendicular to the horizontal plane P H In yet another embodiment, the horizontal plane P H is displaced vertically along the vertical axis A W by at least 1.5 times the distance of the main wing thickness T from the lowest point 128 of the main wing surface V The vertical axis A V is perpendicular to the horizontal plane P H Furthermore, in one or more embodiments, the horizontal plane P H may be displaced vertically along the vertical axis A W by at least 2 times the distance of the main wing thickness T from the lowest point 128 of the main wing surface V The vertical axis A V is perpendicular to the horizontal plane P H In one or more embodiments, in one or more embodiments, the outboard portion 132 of the fairing 130 is such that the first plane P1 is at the horizontal plane P at the third intersection point I3

[0034] In one or more embodiments, the outboard portion 132 of the fairing 130 is such that the first plane P1 is at the horizontal plane P at the third intersection point I3 Hand is configured to intersect with the aerodynamic surface 136' of the outboard portion 132. The third intersection I3 is on the reference line L R It is shifted laterally by a third distance D3 from that point.

[0035] In one or more embodiments, the second plane P2 is aligned with the horizontal plane P at the fourth intersection I4. H and intersects with the aerodynamic surface 136' of the outboard portion 132. The fourth intersection I4 is on the reference line L R It is shifted laterally by a fourth distance D4. In one embodiment, the third distance D3 is longer than the fourth distance D4.

[0036] Multiple embodiments of this disclosure may be described in the context of an aircraft manufacturing and maintenance method 1100, as shown in Figure 6, and an aircraft 1102, as shown in Figure 7. In the pre-manufacturing stage, the maintenance method 1100 may include the specification and design of the aircraft 1102 (block 1104) and the procurement of materials (block 1106). In the manufacturing stage, the components and subassemblies of the aircraft 1102 may be manufactured (block 1108) and system integration (block 1110). The aircraft 1102 may then be licensed and delivered (block 1112) and put into operation (block 1114). During operation, the aircraft 1102 may be scheduled for periodic maintenance and upkeep (block 1116). Periodic maintenance and upkeep may include modifications, reconfigurations, and modifications of one or more systems of the aircraft 1102.

[0037] Each of the processes of Maintenance Method 1100 may be performed or carried out by a system integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military organization, service organization, etc.

[0038] As shown in Figure 7, an aircraft 1102 manufactured by maintenance method 1100 may include a fuselage 1118 having several high-level systems 1120 and interior 1122. Examples of high-level systems 1120 include one or more of the propulsion system 1124, electrical system 1126, hydraulic system 1128, and environmental system 1130. Any number of other systems may be included. Although an example from the aerospace industry has been given, the principles disclosed herein may also be applicable to other industries such as the automotive industry. Therefore, the principles disclosed herein may be applied not only to aircraft 1102 but also to other vehicles such as land vehicles, sea vehicles, and space vehicles.

[0039] One or more systems and methods shown and described herein may be employed in one or more arbitrary stages of the manufacturing and maintenance method 1100. For example, components or subassemblies corresponding to the manufacture of components and subassemblies (block 1108) may be manufactured or produced in a similar manner to components or subassemblies manufactured during the operational period of the aircraft 1102 (block 1114). Also, one or more embodiments of one or more systems and methods, or combinations thereof, may be used in the manufacturing stages, i.e., the manufacture of components and subassemblies (block 1108) and system integration (block 1110), for example, by substantially streamlining or reducing the cost of assembling the aircraft 1102. Similarly, one or more embodiments or combinations thereof that implement a system or method may be used, for example, during the operational period of the aircraft 1102 (block 1114) and / or during maintenance and servicing (block 1116).

[0040] Furthermore, this disclosure includes embodiments as provided for in the following clauses. Article 1. A fairing (130) for an aircraft (100), wherein the aircraft (100) defines a longitudinal central axis (A), and a main wing (120), comprising a leading edge (122), a trailing edge (124) behind the leading edge (122), and a main wing thickness (T WA main wing (120) having a chord (126), and a longitudinal axis (A) aligned vertically with the chord (126). L ) and the longitudinal axis (A) parallel to the longitudinal central axis (A) of the aircraft (100) L The aircraft comprises an engine (110) that defines the horizontal plane (P), a pylon (140) that connects the main wing (120) to the engine (110), and a fairing (130) that covers and supports the pylon (140), wherein the fairing (130) has a horizontal plane (P H ), the longitudinal axis (A L A first plane (P1) perpendicular to the longitudinal axis (A L A second plane (P2) is defined perpendicular to the longitudinal axis (A), and the second plane (P2) is behind the first plane (P1), and the longitudinal axis (A L ) is the horizontal plane (P H When projected onto the baseline (L R ) defines the fairing (130), and the fairing (130) comprises a fairing body (136) that defines an aerodynamic surface (136'), the aerodynamic surface (136') comprises an outboard portion (132) and an inboard portion (134), the inboard portion (134) is (1) the first plane (P1) is the horizontal plane (P H ) and the aerodynamic surface (136') of the inboard portion (134) intersect, (2) the first intersection (I1) is the reference line (L R (3) The second plane (P2) is shifted laterally by a first distance (D1) from the horizontal plane (P H ) and the aerodynamic surface (136') of the inboard portion (134) intersect, (4) the second intersection (I2) is the reference line (L R A fairing (130) is positioned laterally by a second distance (D2) from (5) the first distance (D1), and is configured such that the second distance (D2) is longer than the first distance (D1). Article 2. The fairing (130) according to Clause 1, wherein the inboard portion (134) of the aerodynamic surface (136') has different shape and dimensions from the outboard portion (132) of the aerodynamic surface (136'). Article 3. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is at an angle (θ) of approximately 1 to approximately 10 degrees from the reference line (L R ) the fairing (130) described in Clause 1 or 2 that intersects with the fairing. Article 4. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is at an angle (θ) of approximately 2 to approximately 7 degrees from the reference line (L R ) the fairing (130) described in Clause 1 or 2 that intersects with the fairing. Article 5. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is at an angle (θ) of approximately 3 to 6 degrees relative to the reference line (L R ) the fairing (130) described in Clause 1 or 2 that intersects with the fairing (130). Article 6. The aforementioned chord (126) is the horizontal plane (P H When projected onto the front end (C), a reference segment (C) is defined, and the reference segment (C) is defined on the front end (C L ), rear end (C A ), and the front end (C L ) from the rear end (C A Length up to (C W ) has the length (C) of the reference segment (C) W A fairing (130) as described in any one of clauses 1 to 5, which intersects the aforementioned reference segment (C) at a point located approximately 5% to 15% along the line. Article 7. The aforementioned chord (126) is the horizontal plane (P H When projected onto the front end (C), a reference segment (C) is defined, and the reference segment (C) is defined on the front end (C L ), rear end (C A ), and the front end (C L ) from the rear end (C A Length up to (C WA fairing (130) according to any one of the clauses 1 to 6, having a first plane (P1) that intersects the reference segment (C) at a point located about 10% along the length (CW) of the reference segment (C). Article 8. The aforementioned chord (126) is the horizontal plane (P H When projected onto the front end (C), a reference segment (C) is defined, and the reference segment (C) is defined on the front end (C L ), rear end (C A ), and the front end (C L ) from the rear end (C A Length up to (C W ) has the length (C) of the reference segment (C) W A fairing (130) as described in any one of clauses 1 to 7, which intersects the aforementioned reference segment (C) at a point located approximately 20% to 40% along the line. Article 9. The aforementioned chord (126) is the horizontal plane (P H When projected onto the front end (C), a reference segment (C) is defined, and the reference segment (C) is defined on the front end (C L ), rear end (C A ), and the front end (C L ) from the rear end (C A Length up to (C W ) has the length (C) of the reference segment (C) W A fairing (130) as described in any one of clauses 1 to 8, which intersects the aforementioned reference segment (C) at a point located approximately 30% along the line. Article 10. The horizontal plane (P H ) is the main wing thickness (T W ) at a distance of at least 0.5 times the vertical axis (A V It is shifted vertically along the vertical axis (A V ) is the horizontal plane (P H A fairing (130) perpendicular to any one of the clauses 1 to 9. Article 11. The horizontal plane (P H ) is the main wing thickness (T W ) at a distance of at least 1x the vertical axis (A V It is shifted vertically along the vertical axis (A V ) is the horizontal plane (P H A fairing (130) perpendicular to any one of the clauses 1 to 9. Article 12. The horizontal plane (P H ) is the main wing thickness (T W ) at a distance of at least 1.5 times the vertical axis (A V It is shifted vertically along the vertical axis (A V ) is the horizontal plane (P H A fairing (130) perpendicular to any one of the clauses 1 to 9. Article 13. The horizontal plane (P H ) is the main wing thickness (T W ) at least twice the distance from the lowest point (128) of the main wing surface to the vertical axis (A V It is shifted vertically along the vertical axis (A V ) is the horizontal plane (P H A fairing (130) perpendicular to any one of the clauses 1 to 9. Article 14. The outboard portion (132) is such that (A) the first plane (P1) is at the third intersection (I3) the horizontal plane (P H ) and the aerodynamic surface (136') of the outboard portion (132) intersect, and (B) the third intersection (I3) is the reference line (L R (C) The second plane (P2) is shifted laterally by a third distance (D3) from the horizontal plane (P H ) and the aerodynamic surface (136') of the outboard portion (132) intersect, and (D) the fourth intersection (I4) is the reference line (L RA fairing (130) as described in any one of clauses 1 to 13, configured such that (E) the third distance (D3) is longer than the fourth distance (D4). Article 15. An aircraft equipped with a fairing (130) as described in any one of clauses 1 to 14. Article 16. A method (200) for reducing drag on an aircraft (100) that defines a longitudinal central axis (A), wherein the aircraft (100) is a wing (120) having a leading edge (122), a trailing edge (124) behind the leading edge (122), and a wing thickness (T W A main wing (120) having a chord (126), and a longitudinal axis (A) aligned vertically with the chord (126). L ) and the longitudinal axis (A) parallel to the longitudinal central axis (A) of the aircraft (100) L The aircraft comprises an engine (110) that defines the horizontal plane (P), a pylon (140) that connects the main wing (120) to the engine (110), and a fairing (130) configured to cover and support the pylon (140), wherein the fairing (130) has a horizontal plane (P H ), the longitudinal axis (A L A first plane (P1) perpendicular to the longitudinal axis (A L A second plane (P2) is defined perpendicular to the longitudinal axis (A), and the second plane (P2) is behind the first plane (P1), and the longitudinal axis (A L ) is the horizontal plane (P H When projected onto the baseline (L R The method (200) defines the method and includes arranging the fairing (130) over the pylon (140), the fairing (130) comprising a fairing body (136) defining an aerodynamic surface (136'), the aerodynamic surface (136') comprising an outboard portion (132) and an inboard portion (134), the inboard portion (134) comprising (1) the first plane (P1) at the first intersection (I1) the horizontal plane (P H(1) The plane intersects with the aerodynamic surface (136') of the inboard portion (134), (2) the first intersection (I1) is shifted laterally by a first distance (D1) from the reference line (LR), and (3) the second plane (P2) intersects with the horizontal plane (P H ) and the aerodynamic surface (136') of the inboard portion (134) intersect, (4) the second intersection (I2) is the reference line (L R Method (200), wherein the first is laterally offset by a second distance (D2) from the first, and (5) the second distance (D2) is longer than the first distance (D1). Article 17. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is at an angle (θ) of approximately 1 to approximately 10 degrees from the reference line (L R The method described in Article 16 (200), which intersects with the above. Article 18. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is aligned with a reference line (L) at an angle (θ) of approximately 2 to 7 degrees. R The method described in Article 16 (200), which intersects with the above. Article 19. The first intersection (I1) and the second intersection (I2) define a line (S), and the line (S) is at an angle (θ) of approximately 3 to 6 degrees relative to the reference line (L R The method described in Article 16 (200), which intersects with the above. Article 20. The method according to any one of the clauses 16 to 19 (200), wherein the first intersection (I1) is located at a distance of approximately 10% from the leading edge (122) to the trailing edge (124) with respect to the chord (126). Article 21. The method according to any one of the clauses 16 to 20 (200), wherein the second intersection (I2) is located at a distance of about 20% to about 40% from the leading edge (122) to the trailing edge (124) with respect to the chord (126). Article 22. The method according to any one of the clauses 16 to 21 (200), wherein the second intersection (I2) is located at a distance of approximately 30% from the leading edge (122) to the trailing edge (124) with respect to the chord (126). Article 23. The outboard portion (132) is such that (A) the first plane (P1) is at the third intersection (I3) the horizontal plane (P H ) and the aerodynamic surface (136') of the outboard portion (132) intersect, and (B) the third intersection (I3) is the reference line (L R (C) The second plane (P2) is shifted laterally by a third distance (D3) from the horizontal plane (P H ) and the aerodynamic surface (136') of the outboard portion (132) intersect, and (D) the fourth intersection (I4) is the reference line (L R The method according to any one of the clauses 16 to 22 (200), wherein (E) the third distance (D3) is offset laterally by a fourth distance (D4), and (E) the third distance (D3) is longer than the fourth distance (D4).

[0041] Various embodiments of the (one or more) fairings and (one or more) methods disclosed herein include a variety of components, features, and functions. It should be understood that various embodiments of the (one or more) fairings and (one or more) methods disclosed herein may include, in any combination, any components, features, and functions of any of the other multiple embodiments of the (one or more) fairings and (one or more) methods disclosed herein, and all potential such components, features, and functions are intended to be included within the scope of this disclosure.

[0042] Using the above description and the teachings presented in the accompanying drawings, a number of modifications to the examples specified herein will be conceivable to those skilled in the art to whom this disclosure relates.

[0043] Therefore, it should be understood that this disclosure is not limited to the specific examples illustrated, and that variations and other examples are intended to be included in the accompanying claims. Furthermore, while the embodiments of this disclosure are described in light of specific exemplary combinations of elements and / or functions in the foregoing description and the accompanying drawings, it should be understood that alternative embodiments may provide different combinations of elements and / or functions without departing from the scope of the accompanying claims. Accordingly, the reference numbers in parentheses in the accompanying claims are provided for illustrative purposes only and are not intended to limit the scope of the claimed subject matter to the specific examples provided in this disclosure.

Claims

1. A fairing (130) for an aircraft (100), said aircraft (100) defining a longitudinal axis (A), said wing (120) having a leading edge (122), a trailing edge (124) aft of said leading edge (122), a wing thickness (T W ), and a main wing (120) having a chord (126), a longitudinal axis (A L ) having a longitudinal axis (A) parallel to the longitudinal central axis (A) of the aircraft (100) L ), a pylon (140) connecting the wing (120) to the engine (110), and a fairing (130) supported over the pylon (140), the fairing (130) being in contact with a horizontal plane (P H ), the longitudinal axis (A L ) and the first plane (P 1 ), and the longitudinal axis (A L ) and a second plane (P 2 ) and the second plane (P 2 ) is the first plane (P 1 ) and is located behind the longitudinal axis (A L ) is the horizontal plane (P H ) when projected onto the reference line (L R ), and said fairing (130) defines a fairing body (136) defining an aerodynamic surface (136'), said aerodynamic surface (136') comprising an outboard portion (132) and an inboard portion (134), said inboard portion (134) comprising: The first plane (P 1 ) is the first intersection point (I 1 ) in the horizontal plane (P H ) and intersects with said aerodynamic surface (136') of said inboard portion (134), The first intersection (I 1 ) is a first distance (D 1 ) is shifted laterally, The second plane (P 2 ) is the second intersection point (I 2 ) in the horizontal plane (P H ) and intersects with said aerodynamic surface (136') of said inboard portion (134), The second intersection (I 2 ) is the reference line (L R ) to the second distance (D 2 ) laterally offset, and The second distance (D 2 ) is the first distance (D 1 ) the fairing (130).

2. 2. The fairing of claim 1, wherein the inboard portion of the aerodynamic surface has a different geometry than the outboard portion of the aerodynamic surface.

3. The first intersection (I 1 ) and the second intersection point (I 2 ) defines a line (S), and the line (S) is angled (θ) from about 1 degree to about 10 degrees relative to the reference line (L R 3. The fairing (130) of claim 1 or 2, wherein the fairing (130) intersects with the axially extending ....

4. The first intersection (I 1 ) and the second intersection point (I 2 ) defines a line (S), and the line (S) is angled (θ) from about 2 degrees to about 7 degrees relative to the reference line (L R 2. The fairing (130) of claim 1, wherein the fairing (130) intersects with the axially extending ....

5. The first intersection (I 1 ) and the second intersection point (I 2 ) defines a line (S), and the line (S) is angled (θ) from about 3 degrees to about 6 degrees relative to the reference line (L R 2. The fairing (130) of claim 1, wherein the fairing (130) intersects with the axially extending ....

6. The chord (126) is parallel to the horizontal plane (P H ) defines a reference segment (C), said reference segment (C) having a front end (C L ), posterior end (C A ), and the front end (C L ) to the rear end (C A ) to the length (C W ), and the first plane (P 1 ) is the length (C) of the reference segment (C) W 2. The fairing (130) of claim 1, wherein the fairing (130) intersects the reference segment (C) at a point located about 5% to about 15% along the axis of the fairing (130).

7. The chord (126) is parallel to the horizontal plane (P H ) defines a reference segment (C), said reference segment (C) having a front end (C L ), posterior end (C A ), and the front end (C L ) to the rear end (C A ) to the length (C W ), and the first plane (P 1 ) is the length (C) of the reference segment (C) W 2. The fairing (130) of claim 1, wherein the fairing (130) intersects the reference segment (C) at a point located approximately 10% along the axis of the reference segment (C).

8. The chord (126) is parallel to the horizontal plane (P H ) defines a reference segment (C), said reference segment (C) having a front end (C L ), posterior end (C A ), and the front end (C L ) to the rear end (C A ) to the length (C W ), and the second plane (P 2 ) is the length (C) of the reference segment (C) W 2. The fairing (130) of claim 1, wherein the fairing (130) intersects the reference segment (C) at a point located about 20% to about 40% along the axis of the fairing (130).

9. The chord (126) is parallel to the horizontal plane (P H ) defines a reference segment (C), said reference segment (C) having a front end (C L ), posterior end (C A ), and the front end (C L ) to the rear end (C A ) to the length (C W ), and the second plane (P 2 ) is the length (C) of the reference segment (C) W 2. The fairing (130) of claim 1, wherein the fairing (130) intersects the reference segment (C) at a point located approximately 30% along the axis of the reference segment (C).

10. The outboard section (132) The first plane (P 1 ) is the third intersection (I 3 ) in the horizontal plane (P H ) and intersects with said aerodynamic surface (136') of said outboard portion (132), The third intersection (I 3 ) is the reference line (L R ) to the third distance (D 3 ) is shifted laterally, The second plane (P 2 ) is the fourth intersection (I 4 ) in the horizontal plane (P H ) and intersects with said aerodynamic surface (136') of said outboard portion (132), The fourth intersection (I 4 ) is the reference line (L R ) to the fourth distance (D 4 ) laterally offset, and The third distance (D 3 ) is the fourth distance (D 4 2. The fairing (130) of claim 1, wherein the fairing (130) is configured to be longer than the axial length of ...

Images