Design and Analysis of Aerospike Nozzle to Improve Thrust in Hybrid Rocket Engine
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International Journal of Engineering Trends and Technology (IJETT) |  |
| © 2016 by IJETT Journal | ||
| Volume-36 Number-7 |
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| Year of Publication : 2016 | ||
| Authors : T.Karthikeyan, S.K.Aravindhkumar, J.Arun Kumar |
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| DOI : 10.14445/22315381/IJETT-V36P265 |
Citation
T.Karthikeyan, S.K.Aravindhkumar, J.Arun Kumar"Design and Analysis of Aerospike Nozzle to Improve Thrust in Hybrid Rocket Engine", International Journal of Engineering Trends and Technology (IJETT), V36(7),347-351 June 2016. ISSN:2231-5381. www.ijettjournal.org. published by seventh sense research group
Abstract
The Present Computational Analysis deal with improvement of momentum distribution of the high- temperature exhaust in Rocket Engine through change in profile of aero spike nozzle. Due to change of profile we can improve thrust and mass flow rate of exhaust gas. This analysis is done by using Fluent (ANSYS) on modified profile of Aero spike nozzle. The Comparison has been done with respect to mass flow rate, velocity streamline and vector between unmodified and modified profile. This Profile modification has done on basic aero spike nozzle and this CAD Model designed by CATIA V5.It has been analyzed that due to change profile in exist nozzle area. The new has improved mass flow rate of exhaust gas and also reduced non –uniform exhaust flow.
References
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Keywords
Aero spike, Mass flow rate, Velocity streamline, Velocity vector, Flow analysis.