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Naca Airfoils: NACA 0012
15 to 20
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 | 15 | 0.038 | 1.24 | 32.6 | 0 | 6,000,000 |
| NACA 0012 | 16 | 0.048 | 1.21 | 25.2 | 0 | 6,000,000 |
| NACA 0012 | 18 | 0.075 | 1.05 | 14 | 0 | 6,000,000 |
| NACA 0012 | 20 | 0.11 | 0.92 | 8.4 | 0 | 6,000,000 |
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