Winfoil Airfoils - Total Number: 277
| Name | T/C % | T/C % Chord Position | Camber % | Camber Chord % | CL Max | CD Min |
|---|---|---|---|---|---|---|
| << First < Prev 20 21 22 23 24 Next > Last >> | ||||||
| MH 22 | 7.2 | 28.86 | 1.89 | 33.42 | 0.725 | 0.0048 |
| MH 30 | 7.83 | 29.66 | 1.717 | 44.11 | 0.866 | 0.0039 |
| MH 61 (10.28 %) | 10.24 | 32.154 | 1.365 | 36.787 | 0.841 | 0.0041 |
| MH16 | 12.13 | 41.98 | 1.544 | 53.33 | 0.888 | 0.0059 |
| MH17 | 12.12 | 43.36 | 1.367 | 30.12 | 0.817 | 0.0062 |
Coordinates
| XUpper | YUpper | XLower | YLower |
|---|---|---|---|
| 0.06 | -0.18 | 0.06 | -0.18 |
| 0.09 | 0.24 | 0.61 | -0.57 |
| 0.68 | 0.79 | 1.68 | -0.95 |
| 1.73 | 1.41 | 3.24 | -1.3 |
| 3.22 | 2.06 | 5.3 | -1.57 |
| 5.13 | 2.7 | 7.84 | -1.77 |
| 7.45 | 3.3 | 10.85 | -1.9 |
| 10.16 | 3.85 | 14.31 | -1.97 |
| 13.26 | 4.34 | 18.19 | -1.99 |
| 16.7 | 4.74 | 22.45 | -1.96 |
| 20.47 | 5.04 | 27.03 | -1.9 |
| 24.53 | 5.24 | 31.9 | -1.82 |
| 28.86 | 5.33 | 36.98 | -1.72 |
| 33.42 | 5.33 | 42.21 | -1.62 |
| 38.17 | 5.23 | 47.54 | -1.5 |
| 43.05 | 5.04 | 52.89 | -1.38 |
| 48.02 | 4.76 | 58.22 | -1.25 |
| 53.02 | 4.38 | 63.45 | -1.13 |
| 58.06 | 3.89 | 68.54 | -1 |
| 63.1 | 3.36 | 73.41 | -0.88 |
| 68.07 | 2.83 | 78.01 | -0.76 |
| 72.89 | 2.34 | 82.29 | -0.65 |
| 77.49 | 1.87 | 86.19 | -0.54 |
| 81.81 | 1.46 | 89.68 | -0.44 |
| 85.79 | 1.09 | 92.71 | -0.35 |
| 89.36 | 0.78 | 95.24 | -0.25 |
| 92.48 | 0.53 | 97.26 | -0.15 |
| 95.11 | 0.32 | 98.75 | -0.06 |
| 97.2 | 0.17 | 99.68 | -0.01 |
| 100 | 0 | 100 | 0 |
| X | Y |
|---|---|
| 1 | 0 |
| 0.972 | 0.0017 |
| 0.9511 | 0.0032 |
| 0.9248 | 0.0053 |
| 0.8936 | 0.0078 |
| 0.8579 | 0.0109 |
| 0.8181 | 0.0146 |
| 0.7749 | 0.0187 |
| 0.7289 | 0.0234 |
| 0.6807 | 0.0283 |
| 0.631 | 0.0336 |
| 0.5806 | 0.0389 |
| 0.5302 | 0.0438 |
| 0.4802 | 0.0476 |
| 0.4305 | 0.0504 |
| 0.3817 | 0.0523 |
| 0.3342 | 0.0533 |
| 0.2886 | 0.0533 |
| 0.2453 | 0.0524 |
| 0.2047 | 0.0504 |
| 0.167 | 0.0474 |
| 0.1326 | 0.0434 |
| 0.1016 | 0.0385 |
| 0.0745 | 0.033 |
| 0.0513 | 0.027 |
| 0.0322 | 0.0206 |
| 0.0173 | 0.0141 |
| 0.0068 | 0.0079 |
| 0.0009 | 0.0024 |
| 0.0006 | -0.0018 |
| 0.0006 | -0.0018 |
| 0.0061 | -0.0057 |
| 0.0168 | -0.0095 |
| 0.0324 | -0.013 |
| 0.053 | -0.0157 |
| 0.0784 | -0.0177 |
| 0.1085 | -0.019 |
| 0.1431 | -0.0197 |
| 0.1819 | -0.0199 |
| 0.2245 | -0.0196 |
| 0.2703 | -0.019 |
| 0.319 | -0.0182 |
| 0.3698 | -0.0172 |
| 0.4221 | -0.0162 |
| 0.4754 | -0.015 |
| 0.5289 | -0.0138 |
| 0.5822 | -0.0125 |
| 0.6345 | -0.0113 |
| 0.6854 | -0.01 |
| 0.7341 | -0.0088 |
| 0.7801 | -0.0076 |
| 0.8229 | -0.0065 |
| 0.8619 | -0.0054 |
| 0.8968 | -0.0044 |
| 0.9271 | -0.0035 |
| 0.9524 | -0.0025 |
| 0.9726 | -0.0015 |
| 0.9875 | -0.0006 |
| 0.9968 | -0.0001 |
| 1 | 0 |
| X | Y |
|---|---|
| 100 | 0 |
| 97.2 | 0.17 |
| 95.11 | 0.32 |
| 92.48 | 0.53 |
| 89.36 | 0.78 |
| 85.79 | 1.09 |
| 81.81 | 1.46 |
| 77.49 | 1.87 |
| 72.89 | 2.34 |
| 68.07 | 2.83 |
| 63.1 | 3.36 |
| 58.06 | 3.89 |
| 53.02 | 4.38 |
| 48.02 | 4.76 |
| 43.05 | 5.04 |
| 38.17 | 5.23 |
| 33.42 | 5.33 |
| 28.86 | 5.33 |
| 24.53 | 5.24 |
| 20.47 | 5.04 |
| 16.7 | 4.74 |
| 13.26 | 4.34 |
| 10.16 | 3.85 |
| 7.45 | 3.3 |
| 5.13 | 2.7 |
| 3.22 | 2.06 |
| 1.73 | 1.41 |
| 0.68 | 0.79 |
| 0.09 | 0.24 |
| 0.06 | -0.18 |
| 0.06 | -0.18 |
| 0.61 | -0.57 |
| 1.68 | -0.95 |
| 3.24 | -1.3 |
| 5.3 | -1.57 |
| 7.84 | -1.77 |
| 10.85 | -1.9 |
| 14.31 | -1.97 |
| 18.19 | -1.99 |
| 22.45 | -1.96 |
| 27.03 | -1.9 |
| 31.9 | -1.82 |
| 36.98 | -1.72 |
| 42.21 | -1.62 |
| 47.54 | -1.5 |
| 52.89 | -1.38 |
| 58.22 | -1.25 |
| 63.45 | -1.13 |
| 68.54 | -1 |
| 73.41 | -0.88 |
| 78.01 | -0.76 |
| 82.29 | -0.65 |
| 86.19 | -0.54 |
| 89.68 | -0.44 |
| 92.71 | -0.35 |
| 95.24 | -0.25 |
| 97.26 | -0.15 |
| 98.75 | -0.06 |
| 99.68 | -0.01 |
| 100 | 0 |
V 1.1