Fairing for wing-mounted engines

A method for reducing drag on an aircraft defining a longitudinal centerline axis, the aircraft comprising a wing having a leading edge, a trailing edge aft of the leading edge, a wing thickness, and a wing chord, an engine having a longitudinal axis vertically aligned with the wing chord and parallel to the longitudinal centerline axis of the aircraft, a pylon connecting the wing to the engine, the method comprising:

• positioning a fairing over the pylon, the fairing defining a horizontal plane, a first plane settable perpendicular to the longitudinal axis, and a second plane settable perpendicular to the longitudinal axis, the second plane being aft of the first plane with respect to a direction from the leading edge to the trailing edge of the wing, and a reference line being defined on the horizontal plane as a projections of the longitudinal axis, wherein
• the fairing comprising a fairing body defining an aerodynamic surface, the aerodynamic surface comprising an outboard portion and an inboard portion, the inboard portion being 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 below the wing, aft of the leading edge, and 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 below the wing, aft of the first intersection point, and laterally displaced from the reference line by a second distance, and
• the second distance is greater than the first distance,
• the inboard portion of the aerodynamic surface that is below the wing has a different geometry than the outboard portion of the aerodynamic surface that is below the wing;
• the first intersection point and the second intersection point define a line that intersects the reference line at an angle of about 1 degree to about 10 degrees;
• a reference segment is defined on the horizontal plane as a projection of the wing cord, the reference segment having a leading end, an eft end, and a length from the leading end to the aft end;
• the first plane intersects the reference segment at a point located approximately 5% to approximately 15% along the length of the reference segment;
• and
• the second plane intersects the reference segment at a point located approximately 20% to approximately 40% along the length of the reference segment.

An aircraft defining a longitudinal centerline axis and comprising:

• a wing having a leading edge, a trailing edge aft of the leading edge, a wing thickness, and a wing chord;
• an engine defining a longitudinal axis vertically aligned with the wing chord and parallel with the longitudinal centerline axis of the aircraft;
• a pylon connecting the wing to the engine;
• and
• a fairing positioned over the pylon, the fairing defining a horizontal plane, a first plane settable perpendicular to the longitudinal axis, and a second plane settable perpendicular to the longitudinal axis, the second plane being aft of the first plane with respect to a direction from the leading edge to the trailing edge of the wing, and a reference line being defined on the horizontal plane as a projection of the longitudinal axis,
• wherein:
• the fairing comprises:
• a fairing body defining an aerodynamic surface, the aerodynamic surface comprising an outboard portion and an inboard portion, the inboard portion being 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 below the wing, aft of the leading edge, and 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 below the wing, aft of the first intersection point, and laterally displaced from the reference line by a second distance, and the second distance is greater than the first distance;
• the inboard portion of the aerodynamic surface that is below the wing has a different geometry than the outboard portion of the aerodynamic surface that is below the wing;
• the first intersection point and the second intersection point define a line that intersects the reference line at an angle of between about 1 degree and about 10 degrees;
• a reference segment is defined on the horizontal plane as a projection of the wing cord, the reference segment having a leading end, and aft end, and a length from the leading end to the aft end;
• the first plane intersects the reference segment at a point located approximately 5% to approximately 15% along the length of the reference segment;
• and the second plane intersects the reference segment at a point located approximately 20% to approximately 40% along the length of the reference segment.