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Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameterDesign of injectors and ablative thrust chambers for FLOX propane rocket engine with 1.2 inch throat diameter
Document ID
19690021182
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Pavli, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Peterson, D. A. (NASA Lewis Research Center Cleveland, OH, United States)
Winter, J. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1969
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-5324
Accession Number
69N30560
Funding Number(s)
CONTRACT_GRANT: 128-31-36-02-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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