[restuesaputra]

Hello, im new in fluent
I try to simulate flow over airfoil with 2D simulation using ANSYS Fluent 14.0. I use NACA 0015 as profile. I get convergen solution for AoA 0 till 10 degree, and the value of CL CD that i got is close to the experiment data (error below 10%). But when i want to simulate with high angel of attack above 10 degree (ex: 12, 15 degree) i cant get the solution converge.
Here is the detail of my data:
Re= 1.6e5
AoA= >10 degree (12,15,etc)
Aspect Ratio= 5.4
Area= 0.12464 m^2
Depth= 0.82 m
Length= 0.152 m
Model Solver= Viscous, kw-sst
Convergency criteria= all 1e-5 except k and w are 1e-6
Fluid= air incompressible
Using secon order and secon order upwind and high order

I need your help, cause i want to do validation for my undergraduate thesis I hope get the answer in this thread. Thank you