3.8 Proceedings Paper

Effect of Rocket Propulsion Exhaust on Thermophysical Properties of Graphite Nozzle

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AMER INST PHYSICS
DOI: 10.1063/1.5113280

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The present work deals with effect of rocket propulsion system exhaust on thermophysical properties of graphite nozzle. The thermal properties such as thermal diffusivity, specific heat, thermal conductivity, % expansion and coefficient of thermal expansion (CTE) are determined experimentally in the temperature range 100 to 1000 degrees C and their analysis is presented along with discussion on measurement methods and effect of rocket propulsion exhaust.

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