Vectoring Exhaust Systems for STOL Tactical Aircraft PUBLIC ACCESS

[+] Author Affiliations
R. F. Tape

Rolls-Royce Inc., Atlanta, GA

W. R. Hartill

Rockwell International, Los Angeles, CA

S. Curry

Aero-Propulsion Laboratory, Wright-Patterson AFB, OH

T. J. Jones

Rolls-Royce Limited, Bristol, England

Paper No. 83-GT-212, pp. V002T02A020; 11 pages
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7952-8
  • Copyright © 1983 by ASME


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 1990’s. The exhaust system concepts include side and rear exhaust thrust vectoring systems with axisymmetric and non-axisymmetric 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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