Idea: Creating a convergent-divergent nozzle profile for Mach 1.4 supersonic flow. Guidelines: Give a complete background about the supersonic flow over nozzles and diffusers and the expected flow properties in both cases. Focus should be on nozzle design procedure and associated theories (expansion wave theory, shock waves,..). List the governing equations for the flow and the pressure, temperature, and Mach number relations of flow. Create a code to run the calculation and give an output of the cross-section area of the nozzle at different x-locations. The code should also plot the nozzle profile, plot the variation of Mach number and pressure through the nozzle.