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Flow system startup of a full-scale simulated nuclear rocket enginePerformance of liquid hydrogen flow system during startup transient of nuclear rocket in full scale simulated engine system
Document ID
19650025799
Document Type
Technical Memorandum (TM)
Authors
Colmery, B. H. (NASA Lewis Research Center Cleveland, OH, United States)
Powers, A. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1965
Subject Category
NUCLEAR ENGINEERING
Report/Patent Number
NASA-TM-X-52139
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FLOW CHARACTERISTICS
FUEL FLOW
NUCLEAR ROCKET
LIQUID HYDROGEN
ROCKET ENGINE

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