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Naca Airfoils: NACA 0006
14 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 0006 | 14 | 0.038 | 0.92 | 24.2 | 0 | 6,000,000 |
| NACA 0006 | 16 | 0.06 | 0.85 | 14.2 | 0 | 6,000,000 |
| NACA 0006 | 18 | 0.09 | 0.76 | 8.4 | 0 | 6,000,000 |
| NACA 0006 | 20 | 0.125 | 0.68 | 5.4 | 0 | 6,000,000 |
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