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Design and Evaluation of a Turbojet Exhaust Simulator, Utilizing a Solid-Propellant Rocket Motor, for use in Free-Flight Aerodynamic Research ModelsA method has been developed for modifying a rocket motor so that its exhaust characteristics simulate those of a turbojet engine. The analysis necessary to the design is presented along with tests from which the designs are evaluated. Simulation was found to be best if the exhaust characteristics to be duplicated were those of a turbojet engine at high altitudes and with the afterburner operative.
Document ID
20050019463
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
deMoraes, Carlos A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Hagginbothom, William K., Jr. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Falanga, Ralph A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
December 17, 1954
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-L54I15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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