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RESEARCH PAPERS

Vectoring Exhaust Systems for STOL Tactical Aircraft

[+] Author and Article Information
R. F. Tape

Rolls-Royce, Inc., Atlanta, Ga.

W. R. Hartill

Rockwell International, Los Angeles, Calif.

Lt. S. Curry

Aero-Propulsion Laboratory, Wright-Patterson AFB, Ohio

T. J. Jones

Rolls-Royce Limited, Bristol, England

J. Eng. Power 105(3), 654-662 (Jul 01, 1983) (9 pages) doi:10.1115/1.3227466 History: Received January 04, 1983; Online September 28, 2009

Abstract

An analytical study has been performed to investigate the performance and application of four exhaust nozzle concepts with the potential to enhance the short takeoff and landing capabilities of advanced tactical aircraft for the 1990s. The exhaust system concepts include side and rear exhaust thrust vectoring systems with axisymmetric and nonaxisymmetric nozzles. To investigate the application of the nozzle concepts, advanced tactical aircraft have been configured which will operate from 700 or 1000 feet fields. Four different propulsion system configurations were used, each producing glide slope equilibrium in a different way. The characteristics of these STOL aircraft are compared with those of a CTOL aircraft designed to perform the same mission. The results show that the short field performance can be achieved with little aircraft TOGW or LCC penalty. The study also identifies promising configurations for STOL tactical aircraft.

Copyright © 1983 by ASME
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