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The prediction of large rocket nozzle material performance using a semi-empirical technique.Prediction of large rocket nozzle material performance using semiempirical technique, noting mathematical models for internal and external heat and mass transfer
Document ID
19670051264
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kuby, W. C.
Moody, H. L.
Price, F. C.
Date Acquired
August 3, 2013
Publication Date
January 1, 1967
Subject Category
Propulsion Systems
Accession Number
67A29993
Funding Number(s)
CONTRACT_GRANT: NAS7-408
Distribution Limits
Public
Copyright
Other
Keywords
MASS TRANSFER
ROCKET ENGINE DESIGN
HEAT TRANSFER
REFRACTORY MATERIAL
MATHEMATICAL MODEL
NOZZLE EFFICIENCY

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