Developed a Computational Fluid Dynamics Simulation of the conical converging-diverging nozzle of a solid rocket motor and compared the results of the Compressible Fluid Flow and Gas Dynamics hand calculations. 

The nozzle was modeled after a commercial nozzle from Aerotech Consumer Aerospace.

The model used boundary condition values based on the operating specifiations from Aerotech Consumer Aerospace's website for the nozzle and for the specific propellant mixture.

A 3-dimensional turbulent flow model was created in Siemen's Star-CCM+ Computational Fluid Dynamics software. The region modelled was the entrance to the nozzle, the nozzle exit, and then 5 times the nozzle diameter past the nozzle exit. 

The Nozzle was simulated at a variety of operating conditions from vacuum to 7 MPa to gather most of the operating conditions of a converging diverging nozzle.