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ANSYS Fluent NACA 4412 at Re = 50,000, AoA = 10° – Large CL Differences Between Transition Models and Boundary Conditions

Hi all,

I am working on a final-year CFD project and have been stuck on this for 2 months with no luck investigating a NACA 4412 airfoil at Re = 50,000 and AoA = 10° in ANSYS Fluent 2025 R2. I am trying to reproduce low-Re experimental data before moving on to vortex-generator simulations, but I am getting very different lift predictions depending on the transition model and boundary...