problem reaching convergence for 2D Aerofoil Turbulent FLow
 

Hello all,

I am trying to perform a mesh convergence study on a turbulent 2D aerofoil flow.

A few of the set ups:
-Hybrid mesh using structured inflation layer near the wall and unstructured otherwise
-turbulent flow using SA model with curvature correction
-Re = 2 million at freestream speed of 51.045 m/s. I've edited the air viscosity and increased it to 3.1265e-05 to be able to achieve the correct Re.
- all the other solver parameters are set as default.

Now, as I make the mesh finer, the residuals start to oscilate and I'm unsure whether or not I will ever get the right results. I've attached a few pictures of the mesh and residuals.

Any ideas what may be the issues? I am new in the field of CFD.

EDIT: I've also added CL, CD and CM monitors and whilst CD converges quickly CL and CM don't...