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Cold-air performance evaluation of scale model oxidizer pump-drive turbine for the M-1 hydrogen-oxygen rocket engine. I - Inlet feedpipe-manifold assemblyCold air performance of scale model oxidizer pump drive turbine feedpipe-manifold-nozzle assembly for M-1 rocket engine
Document ID
19660007652
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Evans, D. G. (NASA Lewis Research Center Cleveland, OH, United States)
Roelke, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Stabe, R. G. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
February 1, 1966
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-3294
Report Number: NASA-TN-D-3294
Accession Number
66N16941
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
COLD FLOW TEST
TURBOPUMP
M-1 ROCKET ENGINE
TWO-STAGE TURBINE
TURBINE NOZZLE

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