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Experimental evaluation of high-purity-silica reinforced ablative composites as nozzle sections of 7.8-inch-/19.8 CM/ diameter throat storable-propellant rocket engineHigh purity silica reinforced ablative composite materials evaluated as nozzle sections of throat storable propellant rocket engine - erosion rates and charring
Document ID
19670017957
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Peterson, D. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1967
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TM-X-1391
Report Number: NASA-TM-X-1391
Accession Number
67N27286
Funding Number(s)
CONTRACT_GRANT: 128-31-03-01-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
SILICON OXIDE
ABLATING MATERIAL
STORABLE PROPELLANT
ROCKET NOZZLE

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