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Naca Airfoils: NACA 0018
10 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 0018 | 10 | 0.0155 | 1.07 | 69 | 0 | 6,000,000 |
| NACA 0018 | 12 | 0.0225 | 1.22 | 54.2 | 0 | 6,000,000 |
| NACA 0018 | 14 | 0.034 | 1.33 | 39.1 | 0 | 6,000,000 |
| NACA 0018 | 16 | 0.052 | 1.36 | 26.2 | 0 | 6,000,000 |
| NACA 0018 | 18 | 0.083 | 1.25 | 15.1 | 0 | 6,000,000 |
| NACA 0018 | 20 | 0.12 | 1.08 | 9 | 0 | 6,000,000 |
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