This project covers the observation of the different regimes of flow in a converging nozzle and in a converging diverging nozzle. The parameters that are being observed are the relationships between the pressure ratio vs the distance along the nozzle, the mass flow rate parameter vs the back pressure ratio, and the exit and throat pressure ratio vs the back pressure ratio.

This project’s aim is to demonstrate the validity of the shock wave angles gained from several methods to the shock wave angles gained from Schlieren images. The Solutions covered will be a Computational Fluid Dynamics Solution, a Solution method using a graph of the theta – beta – Mach relation, and an Analytical Solution with an average percentage difference of 10.1505%, 1.59%, and 1.6054% respectively.

The application presented is used to calculate the beta angle in degrees.