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Performance of a variable divergent-shroud ejector nozzle designed for flight mach numbers up to 3.0Pumping and internal thrust performance of simulated variable divergent-shroud ejector nozzle designed for flight Mach numbers to 3.0
Document ID
19650003195
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mihaloew, J. R. (NASA Lewis Research Center Cleveland, OH, United States)
Stofan, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1961
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-255
Report Number: NASA-TM-X-255
Accession Number
65N12796
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
SHROUDED NOZZLE
DIVERGENT NOZZLE
PUMPING

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