[Interstellar]

I am quite new to Ansys Fluent and CFD all together so I am not sure if this is something obvious, but when simulating airflow over a 2D Naca 4412 airfoil using Reynolds number 200'000 and Rans model transitional k-kl-omega, I get values of coefficient of lift and drag very similar to x-foil data and experimental data.

However when I 'extrude' the 2D mesh into the 3D domain and then run the simulation I get a significantly lower lift coefficient. I have adjusted the reference value to be equal to the planform area.
In 2D Simulation I get a cl of 0.44 but in 3D I get 0.29. This is at AOA 0.

In 2D the chord length is 40mm and in 3D the chord length is also 40 mm but length is 40mm making planform reference area 0.0016 m^2.

I've attached links to screenshots of the 3D mesh and results as well as the grid sensitivity I carried out in the 2D sims.
https://docs.google.com/document/d/1...f=true&sd=true, https://docs.google.com/document/d/1...f=true&sd=true