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Naca Airfoils: NACA 2412
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 2412 | 5 | 0.0072 | 0.79 | 109.7 | -0.051 | 6,000,000 |
| NACA 2412 | 6 | 0.0082 | 0.89 | 108.5 | -0.052 | 6,000,000 |
| NACA 2412 | 7 | 0.0094 | 0.99 | 105.3 | -0.053 | 6,000,000 |
| NACA 2412 | 8 | 0.0108 | 1.08 | 100 | -0.054 | 6,000,000 |
| NACA 2412 | 9 | 0.0124 | 1.17 | 94.4 | -0.054 | 6,000,000 |
| NACA 2412 | 10 | 0.0142 | 1.25 | 88 | -0.055 | 6,000,000 |
| NACA 2412 | 11 | 0.0168 | 1.32 | 78.6 | -0.056 | 6,000,000 |
| NACA 2412 | 12 | 0.02 | 1.38 | 69 | -0.057 | 6,000,000 |
| NACA 2412 | 13 | 0.0252 | 1.42 | 56.3 | -0.057 | 6,000,000 |
| NACA 2412 | 14 | 0.031 | 1.45 | 46.8 | -0.058 | 6,000,000 |
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