CFD Analysis on a Different Advanced Rocket Nozzles

  • Prathibha M
  • Gupta M
  • Naidu S
Citations of this article
Mendeley users who have this article in their library.


The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational Efficiency is the key demands on future space transportation systems, like single-stage-to-orbit vehicles (SSTO). The realization of these vehicles strongly depends on the performance of the engines, which should deliver high performance with low system complexity. Performance data for rocket engines are practically always lower than the theoretically attainable values because of imperfections in the mixing, combustion, and expansion of the propellants. The main part of the project addresses different nozzle concepts with improvements in performance as compared to conventional nozzles achieved by Different Mach numbers, thus, by minimizing losses caused by over-or under expansion. The design of different nozzle shapes and flow simulation is done in gambit and fluent software's respectively for various parameters

Author supplied keywords




Prathibha, M., Gupta, M. S., & Naidu, S. (2015). CFD Analysis on a Different Advanced Rocket Nozzles. International Journal of Engineering and Advanced Technology (IJEAT), (6), 2249–8958.

Register to see more suggestions

Mendeley helps you to discover research relevant for your work.

Already have an account?

Save time finding and organizing research with Mendeley

Sign up for free