Oblique shock at the exit of a C-D Nozzle

As a part of my Advanced CFD coursework at MichiganTech, I performed a supersonic airflow simulation through a Convergent-Divergent Nozzle in ANSYS-Fluent. The motive was to model flows from subsonic and gradually take them through supersonic, internal shock, oblique shock, and expansion waves by decreasing the backpressure ratio. The backpressure ratio here is well below 0.68 with laminar and k-omega SST turbulence model settings mapped on a quadrangle mesh. The fluid is an ideal gas entering the nozzle at atmospheric pressure and 0.1 Mach with viscosity a function of the Sutherland three-coefficient method. The image is a converged solution after approx 2000 timesteps.