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Designing for compatibility in high-performance lp engines.Quantitative design criteria for priori injector designs yielding combustion process compatible with thrust chamber-nozzle materials
Document ID
19650046054
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Evans, D. D.
Rupe, J. H.
Date Acquired
August 2, 2013
Publication Date
June 1, 1965
Subject Category
Propulsion Systems
Accession Number
65A28758
Distribution Limits
Public
Copyright
Other
Keywords
PROPELLANT COMBUSTION
LIQUID-LIQUID INTERFACE
COMBUSTION CHAMBER
SPRAY NOZZLE
LIQUID PROPELLANT ROCKET ENGINE
INJECTOR

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