[Louiskhoo]

Guys, recently i am conducting a project which is to simulate a 3D airfoil. However, my lift force cannot stall at higher AOA. The dimension of my airfoil is 127mm chord, 245mm span. Air density 1.225kg/m^3, dynamic viscosity is 1.789e-5. From here, my reynolds number is fully turbulent. Boundary condition for inlet is 133m/s. And also, what kind of model should i use? K epsilon? K omega sst? Or..... Next, for the reference value in setup. Shuld i compute from inlet? Cus some of the video tutorial does not include tht. I nid help, is very urgent.
Thanks
Louiskhoo