Naca Airfoils: NACA_0009
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_0009 | -6 | 0.0078 | -0.62 | -79.5 | 0 | 6,000,000 |
| NACA_0009 | -4 | 0.006 | -0.42 | -70 | 0 | 6,000,000 |
| NACA_0009 | -2 | 0.0052 | -0.21 | -40.4 | 0 | 6,000,000 |
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