[ldavis]

Hi,

I am trying to represent a wing at an altitude of 7924.8 m and a speed of 482 km/h. Therefore, I have values of pressure, temperature and density of 36040Pa, 236.7029K, and 0.53042km/m^3. I have checked these and they should be correct. I put these into FLUENT using material properties/density as a constant value of 0.53042, and the velocity at the inlet boundary. It initializes, but when I try to iterate, I receive the message: "pressure-far-field boundary condition can only be used with ideal gases."

As a result, I changed the material properties/density to "incompressible ideal gas". Under the pressure and velocity boundary conditions, I added the temperature listed above in the thermal properties. This resulted in the correct density. However, despite using an ideal gas law, I still receive the same error message.

I am unsure of what else to change. Please let me know if I am missing another step, or doing something wrong.

Thanks!

[xrs333]

Use ideal gas.