Abstract
Abstract: This report focuses on the design of a 2D theoretical layout of a rocket engine nozzle. Convergent and divergent are to be designed separately with the focus on divergent part for a minimum length nozzle. The divergent part is to be designed using method of characteristics with left and right running characteristics using the known (sonic) values at the throat of the convergent-divergent nozzle. These characteristics would be pressure, density, velocity and temperature. A computer code has been designed to calculate the values of these characteristics and the end characteristics at the exit. CFD analysis has also been carried out on the designed nozzle using commercial software ANSYS.
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