ACA 64(2)-415 [NACA 6a series from Theory of Wing Sections]
n642415 Airfoil (x,y) Coordinates
100 | 0 |
95.032 | 0.976 |
90.066 | 1.982 |
85.092 | 3.02 |
80.109 | 4.062 |
75.115 | 5.084 |
70.111 | 6.055 |
65.096 | 6.954 |
60.072 | 7.762 |
55.04 | 8.456 |
50 | 9.016 |
44.954 | 9.414 |
39.904 | 9.614 |
34.853 | 9.541 |
29.803 | 9.26 |
24.756 | 8.771 |
19.714 | 8.066 |
14.681 | 7.122 |
9.662 | 5.864 |
7.162 | 5.075 |
4.673 | 4.121 |
2.207 | 2.883 |
0.996 | 2.038 |
0.526 | 1.579 |
0.299 | 1.291 |
0 | |
0.701 | -1.091 |
0.974 | -1.299 |
1.504 | -1.61 |
2.793 | -2.139 |
5.327 | -2.857 |
7.838 | -3.379 |
10.338 | -3.796 |
15.319 | -4.43 |
20.286 | -4.882 |
25.244 | -5.191 |
30.197 | -5.372 |
35.147 | -5.421 |
40.096 | -5.33 |
45.046 | -5.034 |
50 | -4.604 |
54.96 | -4.076 |
59.928 | -3.478 |
64.904 | -2.834 |
69.889 | -2.167 |
74.885 | -1.504 |
79.891 | -0.878 |
84.908 | -0.328 |
89.934 | 0.086 |
94.968 | 0.288 |
100 | 0 |
n642415 Airfoil CAD files