NACA 63-012A airfoil
n63012a Airfoil (x,y) Co-ordinates
| 0 | 0 |
| 0.005 | 0.00973 |
| 0.0075 | 0.01173 |
| 0.0125 | 0.01492 |
| 0.025 | 0.02078 |
| 0.05 | 0.02895 |
| 0.075 | 0.03504 |
| 0.1 | 0.03994 |
| 0.15 | 0.04747 |
| 0.2 | 0.05287 |
| 0.25 | 0.05664 |
| 0.3 | 0.05901 |
| 0.35 | 0.05995 |
| 0.4 | 0.05957 |
| 0.45 | 0.05792 |
| 0.5 | 0.05517 |
| 0.55 | 0.05148 |
| 0.6 | 0.047 |
| 0.65 | 0.04186 |
| 0.7 | 0.03621 |
| 0.75 | 0.03026 |
| 0.8 | 0.02426 |
| 0.85 | 0.01826 |
| 0.9 | 0.01225 |
| 0.95 | 0.00625 |
| 1 | 0.00025 |
| 0.95 | -0.00625 |
| 0.9 | -0.01225 |
| 0.85 | -0.01826 |
| 0.8 | -0.02426 |
| 0.75 | -0.03026 |
| 0.7 | -0.03621 |
| 0.65 | -0.04186 |
| 0.6 | -0.047 |
| 0.55 | -0.05148 |
| 0.5 | -0.05517 |
| 0.45 | -0.05792 |
| 0.4 | -0.05957 |
| 0.35 | -0.05995 |
| 0.3 | -0.05901 |
| 0.25 | -0.05664 |
| 0.2 | -0.05287 |
| 0.15 | -0.04747 |
| 0.1 | -0.03994 |
| 0.075 | -0.03504 |
| 0.05 | -0.02895 |
| 0.025 | -0.02078 |
| 0.0125 | -0.01492 |
| 0.0075 | -0.01173 |
| 0.005 | -0.00973 |
| 0 | 0 |
n63012a Airfoil CAD files