NACA 63-010A airfoil
n63010a Airfoil (x,y) Co-ordinates
| 0 | 0 |
| 0.005 | 0.00816 |
| 0.0075 | 0.00983 |
| 0.0125 | 0.0125 |
| 0.025 | 0.01737 |
| 0.05 | 0.02412 |
| 0.075 | 0.02917 |
| 0.1 | 0.03324 |
| 0.15 | 0.0395 |
| 0.2 | 0.044 |
| 0.25 | 0.04714 |
| 0.3 | 0.04913 |
| 0.35 | 0.04995 |
| 0.4 | 0.04968 |
| 0.45 | 0.04837 |
| 0.5 | 0.04613 |
| 0.55 | 0.04311 |
| 0.6 | 0.03943 |
| 0.65 | 0.03517 |
| 0.7 | 0.03044 |
| 0.75 | 0.02545 |
| 0.8 | 0.0204 |
| 0.85 | 0.01535 |
| 0.9 | 0.0103 |
| 0.95 | 0.00525 |
| 1 | 0.00021 |
| 0.95 | -0.00525 |
| 0.9 | -0.0103 |
| 0.85 | -0.01535 |
| 0.8 | -0.0204 |
| 0.75 | -0.02545 |
| 0.7 | -0.03044 |
| 0.65 | -0.03517 |
| 0.6 | -0.03943 |
| 0.55 | -0.04311 |
| 0.5 | -0.04613 |
| 0.45 | -0.04837 |
| 0.4 | -0.04968 |
| 0.35 | -0.04995 |
| 0.3 | -0.04913 |
| 0.25 | -0.04714 |
| 0.2 | -0.044 |
| 0.15 | -0.0395 |
| 0.1 | -0.03324 |
| 0.075 | -0.02917 |
| 0.05 | -0.02412 |
| 0.025 | -0.01737 |
| 0.0125 | -0.0125 |
| 0.0075 | -0.00983 |
| 0.005 | -0.00816 |
| 0 | 0 |
n63010a Airfoil CAD files