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Experimental heat-transfer study of a regeneratively cooled hydrogen-fluorine rocket engine at low chamber pressureHeat-transfer rates and coefficients and coolant pressure loss characteristics in regeneratively cooled liquid hydrogen-liquid fluorine rocket engine thrust chambers
Document ID
19670026338
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Curren, A. N. (NASA Lewis Research Center Cleveland, OH, United States)
Krueger, R. C. (NASA Lewis Research Center Cleveland, OH, United States)
Manning, F. L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Price, H. G., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
September 1, 1967
Subject Category
Thermodynamics And Combustion
Report/Patent Number
NASA-TN-D-4178
Report Number: NASA-TN-D-4178
Accession Number
67N35667
Funding Number(s)
CONTRACT_GRANT: 128-31-06-01-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
PRESSURE DROP
HEAT-TRANSFER COEFFICIENT
LIQUID PROPELLANT ROCKET ENGINE
ROCKET CHAMBER

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