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Naca Airfoils: NACA 23012
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 23012 | 15 | 0.042 | 1.49 | 35.5 | -0.002 | 6,000,000 |
| NACA 23012 | 16 | 0.052 | 1.45 | 27.9 | -0.002 | 6,000,000 |
| NACA 23012 | 18 | 0.082 | 1.25 | 15.2 | -0.002 | 6,000,000 |
| NACA 23012 | 20 | 0.118 | 1.08 | 9.2 | -0.002 | 6,000,000 |
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