XFOIL Version 6.96 Calculated polar for: EPPLER 337 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3815 0.10500 0.10161 -0.0201 1.0000 0.0354 -9.750 -0.3931 0.09995 0.09663 -0.0269 1.0000 0.0360 -9.500 -0.3983 0.09514 0.09186 -0.0315 1.0000 0.0361 -9.250 -0.3881 0.09189 0.08865 -0.0270 1.0000 0.0373 -9.000 -0.3851 0.08855 0.08535 -0.0276 1.0000 0.0377 -8.750 -0.3823 0.08548 0.08233 -0.0281 1.0000 0.0390 -8.500 -0.3877 0.08132 0.07822 -0.0310 1.0000 0.0396 -8.250 -0.3977 0.07736 0.07428 -0.0328 1.0000 0.0400 -8.000 -0.4098 0.07413 0.07106 -0.0325 1.0000 0.0407 -7.750 -0.4228 0.07132 0.06826 -0.0307 1.0000 0.0411 -7.500 -0.4312 0.06838 0.06531 -0.0292 1.0000 0.0418 -7.250 -0.4399 0.06560 0.06247 -0.0271 1.0000 0.0429 -7.000 -0.4457 0.06376 0.06004 -0.0264 0.9800 0.0447 -6.750 -0.4195 0.05600 0.05243 -0.0308 0.9454 0.0460 -6.500 -0.3807 0.05178 0.04810 -0.0362 0.9057 0.0480 -6.250 -0.3544 0.04847 0.04446 -0.0381 0.8611 0.0512 -6.000 -0.3509 0.04691 0.04203 -0.0340 0.8254 0.0557 -5.750 -0.3360 0.04305 0.03818 -0.0334 0.7979 0.0571 -5.500 -0.3216 0.04102 0.03600 -0.0319 0.7741 0.0589 -5.250 -0.3069 0.03926 0.03399 -0.0299 0.7539 0.0623 -5.000 -0.2964 0.03744 0.03160 -0.0265 0.7366 0.0689 -4.750 -0.2787 0.03510 0.02920 -0.0254 0.7194 0.0714 -4.500 -0.2602 0.03374 0.02759 -0.0237 0.7035 0.0767 -3.750 -0.1873 0.02316 0.01516 -0.0157 0.6659 0.0330 -3.500 -0.1586 0.02155 0.01291 -0.0142 0.6538 0.0292 -3.000 -0.1008 0.01866 0.00965 -0.0135 0.6293 0.0289 -2.750 -0.0730 0.01750 0.00841 -0.0131 0.6175 0.0298 -2.500 -0.0484 0.01667 0.00756 -0.0123 0.6074 0.0324 -2.250 -0.0245 0.01613 0.00695 -0.0113 0.5969 0.0371 -2.000 -0.0020 0.01558 0.00639 -0.0100 0.5871 0.0447 -1.750 0.0173 0.01480 0.00564 -0.0081 0.5787 0.0686 -1.500 0.1277 0.01512 0.00885 -0.0186 0.5638 0.9320 -1.250 0.2671 0.01543 0.00865 -0.0391 0.5475 0.9770 -1.000 0.3529 0.01440 0.00736 -0.0509 0.5346 0.9993 -0.750 0.3776 0.01434 0.00713 -0.0507 0.5279 1.0000 -0.500 0.4000 0.01430 0.00702 -0.0500 0.5202 1.0000 -0.250 0.4226 0.01432 0.00688 -0.0493 0.5141 1.0000 0.000 0.4452 0.01431 0.00683 -0.0486 0.5070 1.0000 0.250 0.4680 0.01432 0.00673 -0.0479 0.5006 1.0000 0.500 0.4910 0.01438 0.00670 -0.0473 0.4950 1.0000 0.750 0.5140 0.01441 0.00670 -0.0466 0.4888 1.0000 1.000 0.5370 0.01448 0.00665 -0.0459 0.4834 1.0000 1.250 0.5602 0.01456 0.00670 -0.0453 0.4778 1.0000 1.500 0.5833 0.01462 0.00673 -0.0447 0.4721 1.0000 1.750 0.6067 0.01473 0.00675 -0.0440 0.4675 1.0000 2.000 0.6299 0.01485 0.00686 -0.0434 0.4624 1.0000 2.250 0.6532 0.01494 0.00695 -0.0427 0.4570 1.0000 2.500 0.6767 0.01506 0.00700 -0.0421 0.4525 1.0000 2.750 0.7000 0.01523 0.00716 -0.0415 0.4481 1.0000 3.000 0.7231 0.01535 0.00732 -0.0408 0.4429 1.0000 3.250 0.7465 0.01547 0.00740 -0.0402 0.4382 1.0000 3.500 0.7703 0.01569 0.00754 -0.0396 0.4343 1.0000 3.750 0.7929 0.01584 0.00781 -0.0389 0.4292 1.0000 4.000 0.8161 0.01599 0.00797 -0.0382 0.4246 1.0000 4.250 0.8397 0.01616 0.00808 -0.0376 0.4206 1.0000 4.500 0.8626 0.01640 0.00836 -0.0369 0.4162 1.0000 4.750 0.8850 0.01657 0.00863 -0.0361 0.4112 1.0000 5.000 0.9083 0.01674 0.00880 -0.0355 0.4070 1.0000 5.250 0.9322 0.01701 0.00900 -0.0349 0.4032 1.0000 5.500 0.9535 0.01722 0.00939 -0.0340 0.3981 1.0000 5.750 0.9759 0.01740 0.00961 -0.0332 0.3933 1.0000 6.000 0.9995 0.01760 0.00977 -0.0326 0.3894 1.0000 6.250 1.0209 0.01788 0.01017 -0.0317 0.3846 1.0000 6.500 1.0422 0.01808 0.01047 -0.0307 0.3793 1.0000 6.750 1.0652 0.01822 0.01058 -0.0300 0.3747 1.0000 7.000 1.0861 0.01850 0.01095 -0.0290 0.3695 1.0000 7.250 1.1066 0.01872 0.01129 -0.0278 0.3640 1.0000 7.500 1.1291 0.01889 0.01145 -0.0271 0.3595 1.0000 7.750 1.1493 0.01920 0.01186 -0.0259 0.3545 1.0000 8.000 1.1686 0.01943 0.01223 -0.0246 0.3487 1.0000 8.250 1.1908 0.01954 0.01230 -0.0238 0.3435 1.0000 8.500 1.2079 0.01983 0.01276 -0.0221 0.3371 1.0000 8.750 1.2273 0.01996 0.01296 -0.0208 0.3310 1.0000 9.000 1.2468 0.02020 0.01323 -0.0195 0.3254 1.0000 9.250 1.2626 0.02040 0.01360 -0.0177 0.3184 1.0000 9.500 1.2829 0.02055 0.01369 -0.0165 0.3126 1.0000 9.750 1.2954 0.02082 0.01421 -0.0141 0.3052 1.0000 10.000 1.3128 0.02095 0.01432 -0.0124 0.2986 1.0000 10.250 1.3240 0.02124 0.01481 -0.0098 0.2907 1.0000 10.500 1.3388 0.02141 0.01496 -0.0078 0.2837 1.0000 10.750 1.3469 0.02173 0.01549 -0.0047 0.2754 1.0000 11.000 1.3566 0.02198 0.01576 -0.0018 0.2676 1.0000 11.250 1.3612 0.02231 0.01625 0.0018 0.2589 1.0000 11.500 1.3641 0.02269 0.01669 0.0057 0.2507 1.0000 11.750 1.3629 0.02307 0.01710 0.0103 0.2425 1.0000 12.000 1.3552 0.02351 0.01764 0.0159 0.2347 1.0000 12.250 1.3418 0.02390 0.01801 0.0225 0.2285 1.0000 12.500 1.3317 0.02452 0.01873 0.0278 0.2205 1.0000 12.750 1.3250 0.02542 0.01961 0.0318 0.2124 1.0000 13.000 1.3198 0.02666 0.02092 0.0348 0.2026 1.0000 13.250 1.3152 0.02824 0.02255 0.0369 0.1927 1.0000 13.500 1.3093 0.03019 0.02453 0.0385 0.1835 1.0000 13.750 1.3019 0.03254 0.02689 0.0395 0.1740 1.0000 14.000 1.2947 0.03518 0.02960 0.0401 0.1641 1.0000 14.250 1.2861 0.03811 0.03256 0.0403 0.1556 1.0000 14.500 1.2756 0.04135 0.03579 0.0403 0.1476 1.0000 14.750 1.2662 0.04473 0.03925 0.0400 0.1392 1.0000 15.000 1.2552 0.04825 0.04275 0.0397 0.1324 1.0000 15.250 1.2448 0.05192 0.04649 0.0391 0.1252 1.0000 15.500 1.2342 0.05568 0.05025 0.0384 0.1186 1.0000 15.750 1.2245 0.05947 0.05403 0.0376 0.1127 1.0000 16.000 1.2152 0.06347 0.05811 0.0365 0.1063 1.0000 16.250 1.2062 0.06739 0.06202 0.0354 0.1006 1.0000 16.500 1.1979 0.07142 0.06605 0.0342 0.0950 1.0000 16.750 1.1901 0.07552 0.07024 0.0328 0.0896 1.0000 17.000 1.1831 0.07947 0.07418 0.0316 0.0846 1.0000 17.250 1.1751 0.08382 0.07863 0.0299 0.0793 1.0000 17.500 1.1713 0.08728 0.08204 0.0290 0.0744 1.0000 17.750 1.1636 0.09183 0.08674 0.0271 0.0701 1.0000 18.000 1.1584 0.09576 0.09065 0.0256 0.0660 1.0000