Experimental data are presented showing heat-flux distributions measured calorimetrically with several liquid-propellant rocket thrust-chamber configurations. Thrust levels of the experimental chambers were from 300 to 5000 lb. Enzian-type and axial-stream showerhead propellant injectors were utilized with hydrazine (N2H4) and nitrogen tetroxide (N2O4) propellants. Nozzle-contraction-area ratios of 8 to 1, 4 to 1, and 1.64 to 1 were tested, each having a 5-in. inlet diameter. Characteristic chamber lengths ranged from 16.95 to 62.8 in. The comparison between the experimental heat flux and the analytical heat flux using the method of Bartz [1] was found to be closest in the nozzle-expansion region. The experimental heat-flux measurements ranged between 80 per cent above and 45 per cent below the analytical estimates at the nozzle throat, however. These differences were dependent upon thrust-chamber configuration, injector type, and chamber pressure, and apparently resulted from nonideal combustion and flow characteristics. It is concluded that a priori determination of heat-flux distribution along the thrust-chamber length was possible only to a first approximation for the conditions of these tests.
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A Comparison of Analytical and Experimental Local Heat Fluxes in Liquid-Propellant Rocket Thrust Chambers
William E. Welsh, Jr.,
William E. Welsh, Jr.
Aerospace Corp., El Segundo, Calif.
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Arvel B. Witte
Arvel B. Witte
Jet Propulsion Laboratory, Pasadena, Calif.
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William E. Welsh, Jr.
Aerospace Corp., El Segundo, Calif.
Arvel B. Witte
Jet Propulsion Laboratory, Pasadena, Calif.
J. Heat Transfer. Feb 1962, 84(1): 19-28 (10 pages)
Published Online: February 1, 1962
Article history
Received:
January 3, 1961
Citation
Welsh, W. E., Jr., and Witte, A. B. (February 1, 1962). "A Comparison of Analytical and Experimental Local Heat Fluxes in Liquid-Propellant Rocket Thrust Chambers." ASME. J. Heat Transfer. February 1962; 84(1): 19–28. https://doi.org/10.1115/1.3684282
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