ABSTRACT
Rocket nozzle is a mechanical device designed in such a way as to control the flow rate, direction, velocity, and pressure of the exhaust. In this research paper, Bell nozzle is considered, and the inlet condition to the combustion chamber is varied keeping the design parameters to be the same in each case. Single, double, and four inlets in the combustion chamber is analyzed to estimate the best results in these three cases, and ultimately, a comparative study is done to predict that the single inlet is a better inlet condition for an efficient flow. Emphasis is given on computational fluid dynamics to solve the problem and ANSYS fluent software package is used for the purpose.
