The purpose of this study was to prove the effect of coconut shell nano carbon as a coating for the throat nozzle in order to obtain optimal rocket thrust resistance to thermal temperatures up to 25000C or able to withstand compression or exhaust gas pressure in the throat nozzle up to 80 Kg/cm2. The method used is by comparing experimentally with 3 samples of chamber material, namely the combustion of propellant in the chamber using a nozzle throat diameter of 5mm2 without coconut shell carbon nano coating (NCNCCS), throat nozzle using non-coconut carbon nano coating (CNCNCS), and nozzle throat using coconut shell nanocarbon coating (CNCCS). The results from testing the three samples, the nozzle throat using CNCCS can withstand gas pressure up to 80 Kg/cm2, while NCNCCS with stands gas pressure compression of 60 Kg/cm2 CNCNCS withstands gas pressure compression of 71Kg/cm2. Comparison of nozzle throat using CNCCS produces the most optimal thrust compared to using NCNCCS and CNCNCS

Keywords : Nozzle Throat, Gas Pressure, Thrust, CNCCS.