Naca Airfoils: NACA_23012
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 | -10 | 0.015 | -0.85 | -56.7 | -0.005 | 6,000,000 |
| NACA_23012 | -8 | 0.011 | -0.64 | -58.2 | -0.006 | 6,000,000 |
| NACA_23012 | -6 | 0.008 | -0.42 | -52.5 | -0.008 | 6,000,000 |
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