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Flow system startup of a full-scale simulated nuclear rocket engine.Liquid hydrogen flow system performance during startup transient of nuclear rocket measured in full-scale simulated engine system, approximating in-flight exhaust conditions
Document ID
19660044409
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Colmery, B. H.
Powers, A. G.
Date Acquired
August 3, 2013
Publication Date
February 1, 1966
Subject Category
Nuclear Engineering
Accession Number
66A23699
Distribution Limits
Public
Copyright
Other
Keywords
FLOW MEASUREMENT
LIQUID HYDROGEN
PROPELLANT TESTING
NUCLEAR ROCKET
ROCKET TEST STATION
BOOTSTRAP EQUATION

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