Comparison of Non-Axisymmetric & Axisymmetric Nozzles Installed on a V/STOL Fighter Model 770983

An experimental program sponsored by the Air Force Flight Dynamics Laboratory, utilizing a 1/8th scale advanced twin engine, thrust vectoring V/STOL fighter wind tunnel jet effects model developed for the Naval Air Propulsion Test Center, was completed in June of 1977 at the Arnold Engineering Development Center. The experimental program consisted of three primary parts: (1) measurement of the static internal performance characteristics of several non-axisymmetric nozzles and a baseline axisymmetric nozzle; (2) comparison of the installed dry power performance of the non-axisymmetric nozzles with the axisymmetric nozzles; and (3) measurement of the inflight thrust vectoring propulsion induced aerodynamic effects of the non-axisymmetric nozzle installation. This paper describes the results from parts (1) and (2) of this program. Results from part (3) will be presented in a future publication. The part (2) wind tunnel results indicate major installed performance improvements for the non-axisymmetric nozzles over the conventional axisymmetric nozzles. The overall program produced a significant contribution to the developing non-axisymmetric nozzle/airplane installation data base.


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