Winfoil Airfoils - Total Number: 277
| Name | T/C % | T/C % Chord Position | Camber % | Camber Chord % | CL Max | CD Min |
|---|---|---|---|---|---|---|
| << First < Prev 25 26 27 28 29 Next > Last >> | ||||||
| MH60 | 10.07 | 27.66 | 1.939 | 32.14 | 1.089 | 0.0034 |
| MH61 | 10.25 | 32.15 | 1.365 | 41.57 | 0.842 | 0.0042 |
| MH62 | 9.29 | 27.91 | 1.409 | 37.15 | 0.919 | 0.0056 |
| MILEY | 12.86 | 35.03 | 5.132 | 35.03 | 1.43 | 0.005 |
| NACA 0008 | 7.98 | 30 | 0 | 0 | 0.765 | 0.0064 |
Coordinates
| XUpper | YUpper | XLower | YLower |
|---|---|---|---|
| 0.06 | -0.27 | 0.06 | -0.27 |
| 0.09 | 0.34 | 0.63 | -0.78 |
| 0.63 | 1.1 | 1.76 | -1.31 |
| 1.59 | 1.93 | 3.39 | -1.81 |
| 2.97 | 2.77 | 5.49 | -2.27 |
| 4.75 | 3.58 | 8.05 | -2.66 |
| 6.94 | 4.33 | 11.04 | -2.97 |
| 9.52 | 5 | 14.44 | -3.19 |
| 12.49 | 5.58 | 18.24 | -3.32 |
| 15.81 | 6.05 | 22.4 | -3.37 |
| 19.47 | 6.41 | 26.88 | -3.34 |
| 23.43 | 6.64 | 31.64 | -3.25 |
| 27.66 | 6.75 | 36.64 | -3.1 |
| 32.14 | 6.74 | 41.81 | -2.91 |
| 36.81 | 6.62 | 47.09 | -2.68 |
| 41.64 | 6.38 | 52.44 | -2.44 |
| 46.58 | 6.04 | 57.77 | -2.19 |
| 51.57 | 5.59 | 63.04 | -1.93 |
| 56.58 | 5.06 | 68.16 | -1.68 |
| 61.57 | 4.43 | 73.08 | -1.44 |
| 66.5 | 3.75 | 77.74 | -1.22 |
| 71.33 | 3.04 | 82.09 | -1.01 |
| 76.01 | 2.35 | 86.05 | -0.81 |
| 80.47 | 1.71 | 89.6 | -0.64 |
| 84.64 | 1.15 | 92.68 | -0.49 |
| 88.45 | 0.69 | 95.26 | -0.35 |
| 91.83 | 0.35 | 97.29 | -0.23 |
| 94.69 | 0.13 | 98.77 | -0.12 |
| 98.66 | -0.02 | 99.68 | -0.03 |
| 100 | 0 | 100 | 0 |
| X | Y |
|---|---|
| 1 | 0 |
| 0.9866 | -0.0002 |
| 0.9469 | 0.0013 |
| 0.9183 | 0.0035 |
| 0.8845 | 0.0069 |
| 0.8464 | 0.0115 |
| 0.8047 | 0.0171 |
| 0.7601 | 0.0235 |
| 0.7133 | 0.0304 |
| 0.665 | 0.0375 |
| 0.6157 | 0.0443 |
| 0.5658 | 0.0506 |
| 0.5157 | 0.0559 |
| 0.4658 | 0.0604 |
| 0.4164 | 0.0638 |
| 0.3681 | 0.0662 |
| 0.3214 | 0.0674 |
| 0.2766 | 0.0675 |
| 0.2343 | 0.0664 |
| 0.1947 | 0.0641 |
| 0.1581 | 0.0605 |
| 0.1249 | 0.0558 |
| 0.0952 | 0.05 |
| 0.0694 | 0.0433 |
| 0.0475 | 0.0358 |
| 0.0297 | 0.0277 |
| 0.0159 | 0.0193 |
| 0.0063 | 0.011 |
| 0.0009 | 0.0034 |
| 0.0006 | -0.0027 |
| 0.0006 | -0.0027 |
| 0.0063 | -0.0078 |
| 0.0176 | -0.0131 |
| 0.0339 | -0.0181 |
| 0.0549 | -0.0227 |
| 0.0805 | -0.0266 |
| 0.1104 | -0.0297 |
| 0.1444 | -0.0319 |
| 0.1824 | -0.0332 |
| 0.224 | -0.0337 |
| 0.2688 | -0.0334 |
| 0.3164 | -0.0325 |
| 0.3664 | -0.031 |
| 0.4181 | -0.0291 |
| 0.4709 | -0.0268 |
| 0.5244 | -0.0244 |
| 0.5777 | -0.0219 |
| 0.6304 | -0.0193 |
| 0.6816 | -0.0168 |
| 0.7308 | -0.0144 |
| 0.7774 | -0.0122 |
| 0.8209 | -0.0101 |
| 0.8605 | -0.0081 |
| 0.896 | -0.0064 |
| 0.9268 | -0.0049 |
| 0.9526 | -0.0035 |
| 0.9729 | -0.0023 |
| 0.9877 | -0.0012 |
| 0.9968 | -0.0003 |
| 1 | 0 |
| X | Y |
|---|---|
| 100 | 0 |
| 98.66 | -0.02 |
| 94.69 | 0.13 |
| 91.83 | 0.35 |
| 88.45 | 0.69 |
| 84.64 | 1.15 |
| 80.47 | 1.71 |
| 76.01 | 2.35 |
| 71.33 | 3.04 |
| 66.5 | 3.75 |
| 61.57 | 4.43 |
| 56.58 | 5.06 |
| 51.57 | 5.59 |
| 46.58 | 6.04 |
| 41.64 | 6.38 |
| 36.81 | 6.62 |
| 32.14 | 6.74 |
| 27.66 | 6.75 |
| 23.43 | 6.64 |
| 19.47 | 6.41 |
| 15.81 | 6.05 |
| 12.49 | 5.58 |
| 9.52 | 5 |
| 6.94 | 4.33 |
| 4.75 | 3.58 |
| 2.97 | 2.77 |
| 1.59 | 1.93 |
| 0.63 | 1.1 |
| 0.09 | 0.34 |
| 0.06 | -0.27 |
| 0.06 | -0.27 |
| 0.63 | -0.78 |
| 1.76 | -1.31 |
| 3.39 | -1.81 |
| 5.49 | -2.27 |
| 8.05 | -2.66 |
| 11.04 | -2.97 |
| 14.44 | -3.19 |
| 18.24 | -3.32 |
| 22.4 | -3.37 |
| 26.88 | -3.34 |
| 31.64 | -3.25 |
| 36.64 | -3.1 |
| 41.81 | -2.91 |
| 47.09 | -2.68 |
| 52.44 | -2.44 |
| 57.77 | -2.19 |
| 63.04 | -1.93 |
| 68.16 | -1.68 |
| 73.08 | -1.44 |
| 77.74 | -1.22 |
| 82.09 | -1.01 |
| 86.05 | -0.81 |
| 89.6 | -0.64 |
| 92.68 | -0.49 |
| 95.26 | -0.35 |
| 97.29 | -0.23 |
| 98.77 | -0.12 |
| 99.68 | -0.03 |
| 100 | 0 |
V 1.1