Stub airfoil exhaust nozzle

A gas turbine engine core exhaust nozzle comprising:

• a flow boundary surface and an outlet for discharging combustion exhaust;
• a plurality of circumferentially spaced apart stub airfoils spaced forwardly from said outlet and extending from said flow boundary surface with a span no greater than about a thickness of a local boundary layer of flow thereover;
• and
• each of said airfoils including opposite pressure and suction sides extending in span from root to tip, and extending in chord from leading to trailing edges, and said suction side is convex along said chord to effect flow separation therefrom for shedding vortices along said trailing edge inside said boundary layer.

A gas turbine engine fan exhaust nozzle comprising;

• a flow boundary surface and an outlet for discharging fan air;
• a plurality of circumferentially spaced apart stub airfoils spaced forwardly from said outlet and extending radially inwardly from said flow boundary surface with a span no greater than about a thickness of a local boundary layer of said fan air flow thereover;
• and
• each of said airfoils includes opposite pressure and suction sides extending in span from root to tip, and extending in chord from leading to trailing edges, and said suction side is convex along said chord to effect flow separation therefrom for shedding vortices along said trailing edge inside said fan air boundary layer.