Effect of Rocket Propulsion Exhaust on Thermophysical Properties of Graphite Nozzle

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.