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Naca Airfoils: NACA 23015
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 23015 | 15 | 0.044 | 1.57 | 35.7 | -0.004 | 6,000,000 |
| NACA 23015 | 16 | 0.054 | 1.55 | 28.7 | -0.004 | 6,000,000 |
| NACA 23015 | 18 | 0.085 | 1.38 | 16.2 | -0.004 | 6,000,000 |
| NACA 23015 | 20 | 0.12 | 1.18 | 9.8 | -0.004 | 6,000,000 |
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