If been following along to the video of class 3 and applied all the variables provided in the presentation. Despite applying an Euler BC on the wall, my simulation doesn't show a uniform velocity distribution. Also my shock seems to be more of the oblique type, as there is still a significant amount of supersonic flow behind the kink. This also causes my simulation to take way more iterations than options provided in the test.
Is there something in the video that I missed that might cause this kind of flow?
I suggest you to check the initial solution (Vx = 100 m/s ; Vx=0; Vy = 0 m/s;) and the boundry conditions at the inlet /Vx/V = 1; Vy/V = 0; Vz/V = 0). It seems that the flow at the inlet has not only the x component but also a z or y component that make it create a kind of recirculation area.
Anyway I am a student like you at my first steps on the CFD simulations, so I can be wrong, it is only a friendly suggestion.
Thanks for your suggestion. You were right, I had set the Vz/V = 1 and somehow missed it while verifying my BCs.