Python
A rocket requires high thrust with which it could fly in the sky and outer space which is achieved by convergent divergent nozzle. A convergent-divergent nozzle is a prominent part of rocket such that to provide optimum thrust to drive it into the skies with high velocity. Exhaust gases coming out of the nozzle have supersonic flow i.e., their Mach number is greater than 1. This study computes the flow of gases inside the convergent divergent nozzle using commercially available computational fluid dynamics (CFD) tool ANSYS FLUENT. The CFD analysis is done to calculate the static temperature, static pressure and velocity at the exhaust of the De Laval nozzle. These parameters are calculated theoretically and the results from the CFD are compared. Conclusions are made from the comparison of theoretically obtained values and values got from the CFD analysis.
Design and Analysis of Convergent and Divergent Rocket Nozzle
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