Shock waves for a converging-diverging nozzle and for a rocket

The project is about studying the whole rocket. The work is based on comparing between analytical and theory results on the converging diverging (C-D) nozzle, also called the Laval nozzle for an isentropic flow, a normal shock wave in the diverging section, an oblique shock wave and an expansion at the exit. Then a simulation of the flow at the upper surface of the rocket by CFD will be made, considering the upper area as diamond shaped. The aim of the simulation is to show the oblique shock wave created by supersonic speed and doesn’t intersect with the rest of the rocket, reducing overall the drag