[brucewayne123]

Hello all!

In short, I'm trying to simulate my winglet design in a subsonic (Ma=0.3), incompressible flow.

I kept getting the errors listed on the title of this thread. It seems that my model is diverging.

I'd planned to use hybrid initialization in order to get a more realistic guess, as mentioned by ANSYS, but the errors keep popping out. I had also tried standard initialization and compute from "Inlet", but still getting the floating point exception error.

I'd also checked back my mesh, but the skewness and orthogonal quality seems fine.

One thing I'm not sure is that whether it is due to my usage of pressure far field boundary condition, instead of the using the most general velocity inlet and pressure outlet boundary conditions. Since the maximum speed at subsonic range will achieve Mach number of 0.3, I don't think this is the issue though.

Any advice on how to get my simulation going?

https://www.dropbox.com/s/36chdyit8a...files.zip?dl=0

Edit:
I just noticed that whenever I use hybrid initialization for this case a warning keeps pop out "Warning: flonum_arg detected NaN. Trying to continue with it.". Does anyone know what Fluent mean?