Implementation of CNCCSas a Nozzle Throat Coater to Generate Optimum ofthe Rocket Thrust

Authors : R.Djoko Andreas Navalino; Nur Rachman Supadmana Muda; Budi Santoso

Volume/Issue : Volume 5 - 2020, Issue 11 - November

Google Scholar :

Scribd :

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.


Paper Submission Last Date
30 - November - 2021

Paper Review Notification
In 1-2 Days

Paper Publishing
In 2-3 Days

Never miss an update from Papermashup

Get notified about the latest tutorials and downloads.

Subscribe by Email

Get alerts directly into your inbox after each post and stay updated.

Subscribe by RSS

Add our RSS to your feedreader to get regular updates from us.