Design and numerical analysis on supersonic rocket nozzle

Abstract

Rocket nozzle is part of a rocket in which the burnt propellant from the combustion chamber can exhaust through the nozzle to get the desire amount of thrust and required Mach number. The nozzle turns the static high pressure high temperature gas to low pressure, low temperature, and high velocity gases. To analyse this we have used CFD. Where CFD is the fluid mechanics which is integral part of the design, this is based on numerical methods and algorithm method. To analyse the fluid flow in supersonic rocket nozzle the CFD analysis software is used. Mainly in this work had focused on the pressure, temperature, velocity and Mach number of the mass flow in nozzle by changing the divergent angle. The oblique shock is a main conception and the presence of oblique shock which will create the instabilities. And it is visualized that the shock wave is creating in the nozzle at the 5° of divergent angle and it slowly started eliminating from the nozzle after 5° of divergent angle. To overcome this problem some of the trials are made for different divergent angle such as 5°, 10° 11°, 12°, 15°, and 20°. After 12o of divergent angle the flow parameters will start get reducing. At 20o the sudden drop of flow parameter will occur. By considering all the results at different divergent angle, the 11° angle is more efficient and found all the flow parameters such as velocity, temperature, pressure and Mach number of the mass flow are at required condition.