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Hot-gas-side heat transfer with and without film cooling on a simulated nuclear rocket thrust chamber using H2-O2Heat-transfer coefficients were obtained on a thrust chamber which simulated the geometry of the NERVA nuclear rocket. The tests were performed with and without peripheral film cooling over a chamber pressure range of 1.05 million to 5.84 million newtons per square meter (153 to 847 psia). With no film cooling, the overall axial variation in the value of the correlation coefficient C of the equation (Stanton)* (Prandtl)* to the 0.7ths power = C(Reynolds)* to the -0.2ths power, where * indicates the reference enthalpy condition, was reduced 66 percent when the local diameter in the Reynolds number was replaced by the axial distance from the injector face. The average peak values of C were reduced 25 percent with 2 and 3.75 percent cooling and 50 percent with 7.5 percent cooling.
Document ID
19720009286
Document Type
Other - NASA Technical Note (TN)
Authors
Quentmeyer, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Schacht, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Jones, W. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
February 1, 1972
Subject Category
THERMODYNAMICS AND COMBUSTION
Report/Patent Number
NASA-TN-D-6638
E-6553
Funding Number(s)
PROJECT: RTOP 112-29
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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