Aircraft propulsion system with asymmetric exhaust assembly

An aircraft system, comprising:

• a propulsion system including an aircraft engine, a flowpath and a nacelle;
• the aircraft engine comprising a propulsor rotor, and the propulsor rotor rotatable about an axis and configured to propel air through the flowpath to an airflow exhaust;
• and
• the nacelle housing the aircraft engine and comprising an outer structure with a centerline coaxial with the axis, the outer structure extending axially from a leading edge to a trailing edge, the leading edge disposed at an airflow inlet into the propulsion system, and the trailing edge disposed at the airflow exhaust, wherein at least a section of the trailing edge is angularly offset from the centerline by an acute angle when viewed in a reference plane parallel with the centerline.

An aircraft system, comprising:

• a propulsion system including a turbine engine, an inner flowpath, an outer flowpath and an arcuate lobed mixer;
• the inner flowpath circumscribing an axis, and the inner flowpath extending within the propulsion system to an inner exhaust from the inner flowpath;
• the outer flowpath radially outboard of and circumscribing the inner flowpath, and the outer flowpath extending within the propulsion system to an outer exhaust from the outer flowpath;
• and
• the arcuate lobed mixer arranged radially between and at the inner exhaust and the outer exhaust, the arcuate lobed mixer extending partially circumferentially about the axis, and the arcuate lobed mixer including a plurality of mixer lobes arranged circumferentially about the axis in a circumferentially variably spaced array.