Altitude testing of a flight weight, self-cooled, 2D thrust vectoring exhaust nozzleThe Augmented Deflector Exhaust Nozzle (ADEN) was tested in PSL-3 at NASA-Lewis Research Center using an F404 engine. The ADEN is a flight weight Single Expansion Ramp Nozzle with thrust vectoring, an internal cooling system utilizing the available engine fan flow, and a variable area throat controlled by the engine control system. Test conditions included dry and max A/B operation at nozzle pressure ratios from 2.0 to 15.0. High nozzle pressure loading was simulated to verify structural integrity at near maximum design pressure. Nozzle settings covered the full range in throat area and + or - 15 deg deflection angle. Test results demonstrated expected aerodynamic performance, cooling system effectiveness, control system stability, and mechanical integrity.
Document ID
19850043833
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wooten, W. H. (General Electric Co. Cincinnati, OH, United States)
Blozy, J. T. (General Electric Co. Cincinnati, OH, United States)
Speir, D. W. (General Electric Co. Cincinnati, OH, United States)
Lottig, R. A. (NASA Lewis Research Center Cleveland, OH, United States)