[Lvirgoe]

The goal of this project is to try and reproduce the mach diagrams that I have attached (Results.png). I've attempted to do this in SolidWorks but had little success so I have chosen to download a student version of Ansys.

I am dealing with a supersonic inlet as shown in the attachments (SR71). I'm modeling my current simulation with the geometry shown (AnsysDrawing.jpeg) where the yellow area is considered air (real gas) at Mach 3.2. I'm interested in determining the mach throughout the inlet as well as pressure and temperatures. I'm using the density calculation option and have set the boundary conditions to a velocity inlet with conditions of mach 3.2 and pressure at 80000 feet, pressure outlet, and others as a wall boundary.

In Solidworks this setup is considered an external study and i'm wondering if this should be considered an internal study since I want to find the data within the inlet.

I'd like to know if what I'm currently attempting would be correct and if anyone had suggestions on how to improve my setup or if I am modeling it completely wrong.

Any help is greatly appreciated as I am very new to CFD. I have watched tutorial videos but haven't seen any that would aid in a supersonic inlet spike.