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Naca Airfoils: NACA 0012
5 to 14
NACA airfoil aerodynamic data — lift coefficient, drag coefficient, moment coefficient, and lift-to-drag ratio as functions of angle of attack for standard NACA airfoil profiles
| airfoil id | angle of attack deg | Cd (dimensionless) | Cl (dimensionless) | Cl Cd (dimensionless) | Cm c4 (dimensionless) | reynolds number (dimensionless) |
|---|---|---|---|---|---|---|
| NACA 0012 | 5 | 0.0066 | 0.54 | 81.8 | 0 | 6,000,000 |
| NACA 0012 | 6 | 0.0075 | 0.64 | 85.3 | 0 | 6,000,000 |
| NACA 0012 | 7 | 0.0088 | 0.75 | 85.2 | 0 | 6,000,000 |
| NACA 0012 | 8 | 0.01 | 0.85 | 85 | 0 | 6,000,000 |
| NACA 0012 | 9 | 0.0115 | 0.94 | 81.7 | 0 | 6,000,000 |
| NACA 0012 | 10 | 0.013 | 1.02 | 78.5 | 0 | 6,000,000 |
| NACA 0012 | 11 | 0.0158 | 1.1 | 69.6 | 0 | 6,000,000 |
| NACA 0012 | 12 | 0.019 | 1.17 | 61.6 | 0 | 6,000,000 |
| NACA 0012 | 13 | 0.024 | 1.22 | 50.8 | 0 | 6,000,000 |
| NACA 0012 | 14 | 0.029 | 1.25 | 43.1 | 0 | 6,000,000 |
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