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Naca Airfoils: NACA 4412
5 to 14
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 4412 | 5 | 0.0082 | 0.99 | 120.7 | -0.101 | 6,000,000 |
| NACA 4412 | 6 | 0.0092 | 1.09 | 118.5 | -0.102 | 6,000,000 |
| NACA 4412 | 7 | 0.0105 | 1.19 | 113.3 | -0.102 | 6,000,000 |
| NACA 4412 | 8 | 0.0118 | 1.28 | 108.5 | -0.103 | 6,000,000 |
| NACA 4412 | 9 | 0.0136 | 1.37 | 100.7 | -0.104 | 6,000,000 |
| NACA 4412 | 10 | 0.0155 | 1.44 | 92.9 | -0.105 | 6,000,000 |
| NACA 4412 | 11 | 0.0185 | 1.51 | 81.6 | -0.105 | 6,000,000 |
| NACA 4412 | 12 | 0.022 | 1.56 | 70.9 | -0.106 | 6,000,000 |
| NACA 4412 | 13 | 0.0278 | 1.6 | 57.6 | -0.107 | 6,000,000 |
| NACA 4412 | 14 | 0.034 | 1.62 | 47.6 | -0.107 | 6,000,000 |
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