NACA 0010-34 a=0.8 c(li)=0.2 airfoil
naca001034a08cli0.2 Airfoil (x,y) Coordinates
| 1 | 0.001 |
| 0.95042 | 0.011 |
| 0.90076 | 0.02044 |
| 0.801 | 0.037 |
| 0.70064 | 0.04915 |
| 0.60031 | 0.05735 |
| 0.49994 | 0.06186 |
| 0.39955 | 0.06279 |
| 0.29917 | 0.0598 |
| 0.19886 | 0.05172 |
| 0.14876 | 0.04523 |
| 0.09875 | 0.03637 |
| 0.07378 | 0.03094 |
| 0.04887 | 0.02436 |
| 0.02407 | 0.01608 |
| 0.01176 | 0.01062 |
| 0.00687 | 0.0079 |
| 0 | 0 |
| 0.00813 | -0.00632 |
| 0.01324 | -0.0082 |
| 0.02593 | -0.01186 |
| 0.05113 | -0.01714 |
| 0.07622 | -0.02122 |
| 0.10125 | -0.02445 |
| 0.15124 | -0.02961 |
| 0.20114 | -0.03312 |
| 0.30083 | -0.03684 |
| 0.40045 | -0.03721 |
| 0.50006 | -0.03526 |
| 0.59969 | -0.03131 |
| 0.69936 | -0.02549 |
| 0.799 | -0.0183 |
| 0.89924 | -0.01064 |
| 0.94958 | -0.0061 |
| 1 | -0.001 |
naca001034a08cli0.2 Airfoil CAD files