Simulation of Maximizing the Thrust with Maximization of Nozzle Divergent Section |
Author(s): |
| Mr. N. Vairamuthu , Parisutham Institute of Technology and Science; Mr. T. Anbarasan, Parisutham Institute of Technology and Science; S. Preethi, Parisutham Institute of Technology and Science; P. Martin Raj, Parisutham Institute of Technology and Science |
Keywords: |
| Ansys Fluent, Convergent, Cell Reynolds Number, Mesh, Molecular Prandtl Number |
Abstract |
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The Rocket nozzle is a device which is used to exhaust the gas for propulse the rocket forward and used to control the rate of flow, speed, direction and pressure of stream that exhaust through it. The various type of nozzle is used for rockets depending on the mission requirement. This project contains analysis over a convergent divergent nozzle with reduction of divergent section of a nozzle to perform thrust augumentation process. The aim of this project is to increase thrust and reduction of divergent section of a nozzle. Also, the various contours of nozzle like Cell Equiangle skew, Cell Reynolds number, Pressure, Velocity, Mach Number, and above are calculated at each type of mesh using CFD analysis software ANSYS Fluent. |
Other Details |
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Paper ID: IJSRDV6I70210 Published in: Volume : 6, Issue : 7 Publication Date: 01/10/2018 Page(s): 500-502 |
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