Throat configuration for axisymmetric nozzle

摘要

The radius of the hinged portion of the convergent/divergent axisymmetrical exhaust nozzle of a gas turbine engine is configured at the surface seeing the flow to be contoured at a critical radius so to enhance the flow characteristics of the nozzle and improve the low observable. The liner normally associated with the convergent flap is cut back at the juncture adjacent the hinged point connecting the divergent flap to be below the radar sight at the tail of the engine.