Abstract
The performance of the rocket is determined by atomization, mixing and combustion process. Injectors are used to control these processes. Suitable method should be followed, so that the performance should be increased. The injector implementation in rockets determines the performance of the nozzle that can be achieved. Injectors can be as simple as a number of small diameter holes arranged in carefully constructed patterns through which the fuel and oxidizer travel. The performance of an injector can be improved by either using a superior propellant combustion, increasing the mass flow rate, positioning the angle of the hole or by reducing the size & increasing the number of orifices on the injector plate. In here the position is varied for different angles for injectors to improve the performance of the rocket. The injector is modeled using the Solidworks and a two dimensional combustion analysis to be carried out using ANSYS Fluent for different cases.
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