Airfoil measured from an ASW22 wing
(x,y) Coordinates
| 0 | 0 |
| 0.00228 | 0.01002 |
| 0.00683 | 0.01731 |
| 0.01595 | 0.02642 |
| 0.02506 | 0.03371 |
| 0.03417 | 0.03918 |
| 0.04328 | 0.04465 |
| 0.06606 | 0.05467 |
| 0.08884 | 0.06287 |
| 0.11162 | 0.07016 |
| 0.1344 | 0.07563 |
| 0.15718 | 0.08109 |
| 0.17995 | 0.0852 |
| 0.20273 | 0.0886 |
| 0.22551 | 0.09112 |
| 0.24829 | 0.09294 |
| 0.27107 | 0.09476 |
| 0.29385 | 0.0959 |
| 0.31663 | 0.0969 |
| 0.33941 | 0.0974 |
| 0.36219 | 0.09749 |
| 0.38497 | 0.09749 |
| 0.40774 | 0.0974 |
| 0.43052 | 0.09658 |
| 0.4533 | 0.09567 |
| 0.47608 | 0.0939 |
| 0.49886 | 0.09203 |
| 0.52164 | 0.09021 |
| 0.54442 | 0.088 |
| 0.5672 | 0.08565 |
| 0.58998 | 0.0832 |
| 0.61276 | 0.08018 |
| 0.63554 | 0.0773 |
| 0.65831 | 0.0738 |
| 0.68109 | 0.0705 |
| 0.70387 | 0.06651 |
| 0.72665 | 0.06287 |
| 0.74943 | 0.0585 |
| 0.77221 | 0.05467 |
| 0.79499 | 0.05 |
| 0.81777 | 0.0452 |
| 0.84055 | 0.04009 |
| 0.86333 | 0.0352 |
| 0.8861 | 0.03007 |
| 0.90888 | 0.0247 |
| 0.93166 | 0.0192 |
| 0.95444 | 0.0131 |
| 0.97722 | 0.0068 |
| 1 | 0 |
| 0 | 0 |
| 0.00228 | -0.00547 |
| 0.00683 | -0.01185 |
| 0.01595 | -0.0167 |
| 0.02506 | -0.02005 |
| 0.03417 | -0.02278 |
| 0.04328 | -0.0244 |
| 0.06606 | -0.0288 |
| 0.08884 | -0.03189 |
| 0.11162 | -0.03462 |
| 0.1344 | -0.0362 |
| 0.15718 | -0.03736 |
| 0.17995 | -0.0384 |
| 0.20273 | -0.03918 |
| 0.22551 | -0.0394 |
| 0.24829 | -0.0396 |
| 0.27107 | -0.0396 |
| 0.29385 | -0.0395 |
| 0.31663 | -0.0393 |
| 0.33941 | -0.0389 |
| 0.36219 | -0.03827 |
| 0.38497 | -0.03736 |
| 0.40774 | -0.03645 |
| 0.43052 | -0.03554 |
| 0.4533 | -0.03462 |
| 0.47608 | -0.03371 |
| 0.49886 | -0.0325 |
| 0.52164 | -0.0312 |
| 0.54442 | -0.03 |
| 0.5672 | -0.0284 |
| 0.58998 | -0.0269 |
| 0.61276 | -0.0251 |
| 0.63554 | -0.0229 |
| 0.65831 | -0.0205 |
| 0.68109 | -0.0175 |
| 0.70387 | -0.0144 |
| 0.72665 | -0.01093 |
| 0.74943 | -0.00729 |
| 0.77221 | -0.00364 |
| 0.79499 | 0 |
| 0.81777 | 0.00273 |
| 0.84055 | 0.00456 |
| 0.86333 | 0.00547 |
| 0.8861 | 0.00547 |
| 0.90888 | 0.00547 |
| 0.93166 | 0.0048 |
| 0.95444 | 0.00364 |
| 0.97722 | 0.0018 |
| 1 | 0 |
DU84132V airfoil CAD files