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Coolant-side heat-transfer rates for a hydrogen-oxygen rocket and a new technique for data correlationAn experimental investigation was conducted to determine the coolant-side, heat transfer coefficients for a liquid cooled, hydrogen-oxygen rocket thrust chamber. Heat transfer rates were determined from measurements of local hot gas wall temperature, local coolant temperature, and local coolant pressure. A correlation incorporating an integration technique for the transport properties needed near the pseudocritical temperature of liquid hydrogen gives a satisfactory prediction of hot gas wall temperatures.
Document ID
19730010241
Document Type
Other - NASA Technical Note (TN)
Authors
Schacht, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Quentmeyer, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1973
Subject Category
THERMODYNAMICS AND COMBUSTION
Report/Patent Number
NASA-TN-D-7207
E-7204
Funding Number(s)
PROJECT: RTOP 503-35
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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NameType 19730010241.pdf STI