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Experimental rocket performance of Apollo storable propellants in engines with large area ratio nozzlesNitrogen tetroxide and blend of hydrazine and unsymmetrical dimethyl hydrazine evaluated in rocket engines with large area ratio nozzles - Apollo project
Document ID
19660024164
Document Type
Other - NASA Technical Note (TN)
Authors
Aukerman, C. A. (NASA Lewis Research Center Cleveland, OH, United States)
Trout, A. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1966
Subject Category
Propellants
Report/Patent Number
NASA-TN-D-3566
Accession Number
66N33454
Funding Number(s)
CONTRACT_GRANT: 104-31-02-01-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
STORABLE PROPELLANT
APOLLO PROJECT
HYDRAZINE
NITROGEN OXIDE
ROCKET NOZZLE

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