Open rotor pylon fairing

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end, the aircraft comprising:

• a fuselage extending between the forward end of the aircraft and the aft end of the aircraft;
• a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage;
• an unducted turbofan engine having an unducted fan including unducted fan blades rotatable about the longitudinal centerline and unducted fan guide vanes not rotatable about the longitudinal centerline, the unducted fan guide vanes having a leading edge and a trailing edge;
• and
• a pylon fairing that connects the unducted turbofan engine to the wing assembly and the pylon fairing defining a forwardmost point, the pylon fairing defining a lengthwise direction, a leading edge, a trailing edge, a first chord extending from the leading edge to the trailing edge at a first position along the lengthwise direction, and a second chord extending from the leading edge to the trailing edge at a second position along the lengthwise direction, the pylon fairing including a first maximum thickness portion at a first percentage of the first chord and a second maximum thickness portion at a second percentage of the second chord, wherein the first percentage is different than the second percentage, wherein the first maximum thickness portion is located between 40% and 60% of the first chord from the leading edge and the second maximum thickness portion is located between 20% and 40% of the second chord from the leading edge, wherein the second position is closer to the unducted turbofan engine than the first position, wherein the unducted turbofan engine includes a forward compressor frame having a mount, wherein the forwardmost point of the pylon fairing is upstream of the mount of the forward compressor frame, and wherein the forwardmost point of the pylon fairing is upstream of the leading edge of the unducted fan guide vanes.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end, the aircraft comprising:

• a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft;
• a first wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage;
• a first unducted turbofan engine having an unducted fan including unducted fan blades rotatable about the longitudinal centerline and unducted fan guide vanes not rotatable about the longitudinal centerline, the unducted fan guide vanes having a leading edge and a trailing edge;
• and
• a first pylon fairing that connects the first unducted turbofan engine to the first wing assembly and the first pylon fairing defining a forwardmost point, the first pylon fairing having a first pressure side and a first suction side, the first pressure side of the first pylon fairing defining a first shape, and the first suction side of the first pylon fairing defining a second shape different than the first shape, wherein the first pylon fairing defines a lengthwise direction, a leading edge, a trailing edge, and a chord extending from the leading edge to the trailing edge, and wherein the first shape and the second shape are different at a common location along the lengthwise direction of the first pylon fairing, and wherein the first wing assembly extends laterally outwardly with respect to the longitudinal centerline from a starboard side of the fuselage,
• wherein the first unducted turbofan engine includes a forward compressor frame having a mount, wherein the forwardmost point of the first pylon fairing is upstream of the mount of the forward compressor frame, and wherein the forwardmost point of the first pylon fairing is upstream of the leading edge of the unducted fan guide vanes.