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Naca Airfoils: NACA 23015
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 23015 | 5 | 0.0074 | 0.79 | 106.8 | -0.009 | 6,000,000 |
| NACA 23015 | 6 | 0.0085 | 0.9 | 105.9 | -0.008 | 6,000,000 |
| NACA 23015 | 7 | 0.01 | 1.01 | 101 | -0.008 | 6,000,000 |
| NACA 23015 | 8 | 0.0115 | 1.11 | 96.5 | -0.007 | 6,000,000 |
| NACA 23015 | 9 | 0.0134 | 1.21 | 90.3 | -0.006 | 6,000,000 |
| NACA 23015 | 10 | 0.0155 | 1.31 | 84.5 | -0.006 | 6,000,000 |
| NACA 23015 | 11 | 0.0188 | 1.4 | 74.5 | -0.005 | 6,000,000 |
| NACA 23015 | 12 | 0.0225 | 1.48 | 65.8 | -0.005 | 6,000,000 |
| NACA 23015 | 13 | 0.0285 | 1.54 | 54 | -0.004 | 6,000,000 |
| NACA 23015 | 14 | 0.035 | 1.58 | 45.1 | -0.004 | 6,000,000 |
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