Abstract
A brief review of methods of uti l iz ing liquid propellants as roeket-motor coolants is given, and criteria for acceptable cooling are established. Methods of analytical and experimental determinat ion of the pertinent heat-transfer characteristics of propellants are described. The measured m a x i m u m rates at which l iquid a m m o n i a can satisfactorily accept heat are presented to show typical trends wi th variations of fluid pressure, temperature and velocity. Measured m a x i m u m rates for several propellants are c o m pared wi th predictions of heat fluxes from the combust ion gases of these propellants when producing the same thrust in a hypothetical rocket motor . From this comparison, an ins ight into the importance of various propellant properties and operating condit ions is gained.
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