Abstract
In rocket, a nozzle is used to control mass flow rate, velocity distribution and pressure of the exhaust gas that emerges out from the combustion chamber. The nozzle is used to alchemize the chemical and thermal energy generated in the combustion chamber into thrust. The nozzle metamorphoses the high pressure, high temperature, low velocity gas in the combustion chamber into high velocity, low pressure and temperature. The design of nozzle is an important aspect for achieving the maximum Mach number and minimum turbulent intensity. In this study, the numerical investigation is done at different divergent angles to find the effect of divergent angle on Mach number and static pressure. The different divergent angles used for analysis are 9°, 12°, 15° and 18°. The inlet boundary conditions were specified according to the available experimental information. The results evaluated and compared with the help of different contours and graphs to figure out the optimum divergent angle with maximum Mach number.
