Volume No. 5 Issue No.: 2 Page No.: 308-321 October-December 201

 

CFD ANALYSIS OF A ROCKET NOZZLE WITH TWO INLETS AT MACH 2.1

 

K. M. Pandey*1 and S. K. Yadav2

1. Department of Mechanical Engineering, N.I.T Silchar, Assam (INDIA)
2. Department of Mechanical Engineering, Gurgaon College of Engineering, Gurgaon (INDIA)

 

Received on : July 5, 2010

 

ABSTRACT

 

In this paper CFD analysis of pressure and temperature for a rocket nozzle with two inlets at Mach 2.1 is analyzed with the help of fluent software. When the fuel and air enter in the combustion chamber according to the x and y plot, it is burning due to high velocity and temperature and then temperature increases rapidly in combustion chamber and convergent part of the nozzle and after that temperature decreases in the exit part of the nozzle. It is concluded in this paper that two inlet rocket nozzle is having better performance than single inlet.

 

Keywords : Rocket nozzle, Total temperature, Static temperature, Mach number, Total pressure, Throat

 

 

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