Gas turbine exhaust nozzle noise abatement

An aircraft, comprising:

• a fuselage, a wing and a turbofan engine, the turbofan engine including a turbine section and an exhaust nozzle disposed downstream from the turbine section, wherein the exhaust nozzle comprises:
• a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end, wherein each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root;
• wherein at least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip, and wherein the inner wall extends along the first segment, the second segment and the third segment, wherein the first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment;
• wherein the inner wall along the first segment has a radius that is constant with respect to the axial centerline from the root to a first inflection point, the inner wall along the second segment has an increasing radius from the first inflection point to a second inflection point, and the inner wall along the third segment has a decreasing radius from the second inflection point to the tip, wherein the inner wall at the root defines a root radius, and wherein the inner wall at the tip defines a tip radius that is less than the root radius;
• and
• wherein the outer wall of the at least one chevron includes a first outer wall segment that has a first increasing radius extending from the tip to a first outer wall inflection point and a second outer wall segment that has a second increasing radius extending from the first outer wall inflection point to an outer wall upstream end that extends beyond the downstream end of the nozzle body, and wherein the first outer wall inflection point is located between the second inflection point of the inner wall and the tip of the chevron.