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NACA0012 airfoil

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The NACA 0012 airfoil is widely used. The simple geometry and the large amount of wind tunnel data provide an excellent 2D validation case. For this case I use the Spalart-Allmaras turbulence model.


Naca0012 mesh final.JPG

The mesh is a 30,000 cell C-grid. The width off the first cell at the foil boundary is 0.02 mm. At Re = 3e6 this results in a wall y+ = 1.3 ± 0.4 . The mesh shown is for an Angle of Attack of 6 degrees.

Drag Coefficient

Naca0012 cd tripwire.JPG

The drag coefficient at zero Angle of Attack depends on the Reynold's number. The experimental data is for an airfoil with a trip wire that forces the experimental boundary layer to be completely turbulent.[1] This corresponds to the Fluent model, which has an active turbulence model over the complete airfoil.

Lift Curve

Naca0012 lift curve.JPG

The lift coefficient depends on the Angle of Attack. For Re = 2e6 I compare the lift coefficient to experimental results.[2]

Lift Curve Slope

Naca0012 lift curve slope.JPG

The initial slope of the lift curve depends on the Reynold's number. Here I compare the lift curve slope to experimental results.[1]


1. W. J. McCroskey, A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil, NASA Technical Memorandum 10001 9 (1987)
2. L. Lazauskus, NACA 0012 Lift Data

My wiki