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Exhaust Nozzles for Supersonic Flight with Turbojet EnginesGood internal performance over a wide range of flight conditions can be obtained with either a plug nozzle or a variable ejector nozzle that can provide a divergent shroud at high pressure ratios. For both the ejector and the plug nozzle, external flow can sometimes cause serious drag losses and, for some plug-nozzle installations, external flow can cause serious internal performance losses. Plug-nozzle cooling and design of the secondary-air-flow systems for ejectors were also considered .
Document ID
20090024829
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Shillito, Thomas B. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Hearth, Donald P. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Cortright, Edgar M. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
January 18, 1956
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E56A18
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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