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Altitude Testing of a Flight Weight, Self-Cooled, 2D Thrust Vectoring Exhaust Nozzle
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Abstract
The 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 (SERN) 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 ±15° deflection angle. Test results demonstrated expected aerodynamic performance, cooling system effectiveness, control system stability, and mechanical integrity.
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Wooten, W., Blozy, J., Speir, D., and Lottig, R., "Altitude Testing of a Flight Weight, Self-Cooled, 2D Thrust Vectoring Exhaust Nozzle," SAE Technical Paper 841557, 1984, https://doi.org/10.4271/841557.Also In
References
- AIAA Paper No. 74-1169 Exhaust Nozzle Deflector Systems for V/STOL Fighter Aircraft Lander J. A. General Electric Company Palcza J. Lawrence Naval Air Propulsion Test Center October 21 1974
- AIAA Paper No. 75-1318 Augmented Deflector Exhaust Nozzle (ADEN) Design for Future Fighters Lander J. A. Nash D. O. General Electric Company Palcza J. Lawrence Naval Air Propulsion Test Center September 29 1975
- ASME Paper No. 77-GT-110 Structural and Cooling Aspects of the ADEN Nonaxisymmetric Exhaust Nozzle Nash D. O. Wakeman T. G. General Electric Company Palcza J. L. Naval Air Propulsion Test Center March 27 1977