I'm trying to run supersonic flow simulations around a 3D rocket body. I'm simulating a quarter of the geometry with symmetry applied on the side faces. When I have run the simulation with 100 iterations, my output is showing uniform pressure nearly everywhere throughout the flow without even a hint of a shock wave or skin friction. This model isn't trying to be very accurate, but I refined the mesh significantly around the rocket to try and see if I could get a change.
I am using Fluent with the steady density-based solver (although I got the same result with the steady pressure-based solution). Energy was enabled, and the viscous solver with the Transition SST model was used. Conditions approximate an altitude of around 30000 ft, so the material is air with density 0.449 kg m^-3 and viscosity 1.6e-5 kg m^-1 s^-1. Operating pressure is 30 kPa, and temperature is -40 degrees Celsius. The flow speed is 600 m/s. I have attached an image with the results. The rocket body is defined as a wall, as is the farfield (the long curved piece on top).
In the above geometry, the flat face closest to the camera (shaped like a baseball field) is the inlet. Flow is heading in the negative x direction (but even if it were positive, there should still not be uniform pressure).
Any thoughts about what is causing this would be greatly appreciated. Thanks a lot!