Ansys Fluent - Airfoil 3D (NACA 4412)
Written by cfd.ninja
The NACA 4412 is a cambered profile that produces lift at zero angle of attack, which makes it a good case for checking that your setup reproduces known aerodynamic behaviour.
In three dimensions the wing differs from the 2D profile in one essential way: the tip vortex. Air spills from the pressure side to the suction side around the tip, and the induced drag that follows has no 2D equivalent. That is why a 3D lift coefficient comes out lower than the 2D one for the same angle of attack.
For the numbers to mean anything, the reference values in Fluent must match the case: the area, the chord length and the incoming velocity. Get those wrong and the lift and drag coefficients are wrong by a constant factor even if the flow field is perfect. On the mesh side, the boundary layer on the wing needs inflation sized from your target y+, which you can estimate with the Y+ calculator.
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