Ansys Fluent - NACA Airfoil 4412
Written by cfd.ninja
This is the two dimensional version of the NACA 4412 case, and it is the cheapest way to check that a setup reproduces known aerodynamic data before spending time on a 3D wing.
In 2D there is no tip and therefore no induced drag, so the lift coefficient comes out higher than for a finite wing at the same angle of attack. The drag is only friction plus pressure drag on the section itself.
Two things decide whether your numbers land near the published data: the reference values, which for a 2D case use the chord as the area, and the near-wall mesh. The turbulence model expects a particular y+ range, and the first cell height is what puts you there. Estimate it with the Y+ calculator.
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