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Naca Airfoils: NACA 23012
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 23012 | 5 | 0.007 | 0.76 | 108.6 | -0.007 | 6,000,000 |
| NACA 23012 | 6 | 0.008 | 0.87 | 108.8 | -0.006 | 6,000,000 |
| NACA 23012 | 7 | 0.0094 | 0.98 | 104.3 | -0.006 | 6,000,000 |
| NACA 23012 | 8 | 0.0108 | 1.08 | 100 | -0.005 | 6,000,000 |
| NACA 23012 | 9 | 0.0126 | 1.18 | 93.7 | -0.004 | 6,000,000 |
| NACA 23012 | 10 | 0.0145 | 1.28 | 88.3 | -0.004 | 6,000,000 |
| NACA 23012 | 11 | 0.0176 | 1.36 | 77.3 | -0.003 | 6,000,000 |
| NACA 23012 | 12 | 0.021 | 1.43 | 68.1 | -0.003 | 6,000,000 |
| NACA 23012 | 13 | 0.0268 | 1.48 | 55.2 | -0.002 | 6,000,000 |
| NACA 23012 | 14 | 0.033 | 1.52 | 46.1 | -0.002 | 6,000,000 |
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