CFD Analysis of a Rocket Nozzle withFour Inlets at Mach 2.1.

Parasa Lakshmana Kumar

Abstract


In this work CFD investigation of weight and temperature for a rocket spout with four channels at Mach 2.1 is examined with the assistance of familiar programming. at the point when the fuel and air enter in the ignition chamber as indicated by the x and y plot, it is smoldering because of high speed and temperature and afterward temperature increments quickly in burning chamber and joined a portion of the spout and after that temperature diminishes in the way out some portion of the spout. it is deduced in this paper Four gulf rocket spout is having preferred execution over single channel and two delta as seen from the past exploration work done.

Keywords


CFD1, examined2, ignition3, temperature4.

References


Boris M. Kiforenko, Zoya V. Pasechnik and IgorYu. Vasil’ev,“Comparison of the rocket engines efficiency in the case of low thrust orbit-to-orbit transfersâ€, ActaAstronauticaVol 60, 2007,pp- 801-809.

ZhigangFeng and QiWang “Research on health evaluation system of liquid-propellant rocket engine ground-testing bed based on fuzzy theoryâ€, ActaAstronauticaVol 61,2007, pp-840-853.

VadimZakirov and Vladimir Pavshook; “Russian Nuclear Rocket Engine Design for Mars Explorationâ€, Tsinghua Science And Technology.,Vol 12, 2007, pp-256-260.

Johannes Lux , Dmitry Suslov and Oskar Haidn, “porous liquid propellant rocket engine injectorsâ€, Aerospace Science and Technology, Vol 12, 2007, pp-469-477.

Alexander Potapov, YuriyShtefan and Elena Lichman, “Research of material for un cooled nozzle extensions of liquid rocket enginesâ€, Acta Astronautica, Vol 64, 22-27.

G. Lacaze, B. Cuenot, T. Poinsot and M. Oschwald, “Large eddy simulation of laser ignition and compressible reacting flow in a rocket-like configurationâ€, Combustion and Flame, Vol 156,

,PP-1166-1180.

ValeriyI.Timoshenkoa,IgorS.Belotserkovetsa,Vjacheslav,P.Gusininb, “Problems of providing completeness of the methane-containing block-jet combustion in a rocket-ramjet engine’s combustion chamberâ€, ActaAstronautica, Vol 65, 2009, pp-231-1237.

M. Masquelet, S. Menona, Y. Jinband R. Friedrich, “Simulation of unsteady combustion in a LOX-GH2 fueled rocket engineâ€, Aerospace Science and Technology Vol 13, 2009, pp-466-474.

David R. Greatrix, Regression rate estimation for standard-flow hybrid rocket engines, Aerospace Science and Technology 13, 358-363, (2009).

K.M.Pandey and S.K.Yadav, “CFD Analysis of a Rocket Nozzle with Two Inlets at Mach 2.1â€, Journal of Environmental Research and Development, Vol 5, No 2, 2010, pp- 308-321,


Full Text: PDF [FULL TEXT]

Refbacks

  • There are currently no refbacks.


Copyright © 2013, All rights reserved.| ijseat.com

Creative Commons License
International Journal of Science Engineering and Advance Technology is licensed under a Creative Commons Attribution 3.0 Unported License.Based on a work at IJSEat , Permissions beyond the scope of this license may be available at http://creativecommons.org/licenses/by/3.0/deed.en_GB.

Â