CFD Analysis on a Different Advanced Rocket Nozzles
Munipally Prathibha1, M. Satyanarayana Gupta2, Simhachalam Naidu3

1Munipally Prathibha, Vajpayee Nagar, Chinthal, H. M. T. Road, Quthbullapur (m), Ranga Reddy, Hyderabad (Telangana), India.
2M. Satyanarayana Gupta, Vajpayee Nagar, Chinthal, H. M. T. Road, Quthbullapur (m), Ranga Reddy, Hyderabad (Telangana), India.
3Simhachalam Naidu, Vajpayee Nagar, Chinthal, H. M. T. Road, Quthbullapur (m), Ranga Reddy, Hyderabad (Telangana), India.

Manuscript received on 15 August 2015 | Revised Manuscript received on 25 August 2015 | Manuscript Published on 30 August 2015 | PP: 14-22 | Volume-4 Issue-6, August 2015 | Retrieval Number: F4144084615/15©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)

Abstract: 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
Keywords: Launcher Reliability, Future Space Transportation Systems, Theoretically Attainable, Mixing, Combustion, And Expansion.

Scope of the Article: Structural Reliability Analysis