Gas-cycle nuclear-rocket power plants with hydrogen as propellant are considered as propulsion devices for space vehicles; summary of analysis conducted over range of reactor power of 46 to 1600 Mw; analysis of local heat-flux capability of coolant at nozzle throat indicated that cooling capability was inadequate to maintain wall temperature of 1440 R; techniques for improving capability such as h-p drop, high wall temperature, refractory wall coatings, etc.
Analysis of nuclear-rocket nozzle cooling
NASA -- Tech Note
1960
24 pages
Report
English
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An analysis of nuclear-rocket nozzle cooling
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