[NithinHM]

Hello everyone,
I am a student trying to do my project on 2D analysis of airfoil, I have selected a supercritical airfoil I.e whitcomb super integral airfoil (http://airfoiltools.com/airfoil/deta...il=whitcomb-il )
I have done my meshing in GAMBIT and imported it in ansys fluent in mesh format
Which is a C type grid

Chord length=1.436 metre
Velocity =254m/s
Mach no= 0.85
Density=0.389
Viscosity=14.4e-6

Using a pressure based solver
And with Spalart Allmaras equation

When I am initialising and Running the calculations my continuity equation is diverging. I have tried changing my mesh but it still converges. I don’t know where I am going wrong.
Can you please help me with my problem

Sorry and thanks for you help

[vinerm]

If M = 0.85, why is density constant? For M >= 0.3, flow is always compressible, therefore, density should be based on ideal or real gas.