XFOIL Version 6.96 Calculated polar for: FX 63-110 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3491 0.08945 0.08613 -0.0371 1.0000 0.0614 -8.000 -0.3653 0.08818 0.08494 -0.0341 1.0000 0.0628 -7.750 -0.3864 0.08729 0.08415 -0.0305 1.0000 0.0632 -7.500 -0.3793 0.06891 0.06564 -0.0718 0.9841 0.0678 -7.250 -0.3615 0.07420 0.07110 -0.0515 0.9853 0.0697 -7.000 -0.3374 0.07139 0.06827 -0.0542 0.9799 0.0723 -6.750 -0.3049 0.05262 0.04893 -0.0937 0.9646 0.0813 -6.500 -0.2640 0.03656 0.03177 -0.1088 0.9606 0.0553 -6.250 -0.2279 0.03160 0.02626 -0.1141 0.9554 0.0552 -6.000 -0.1884 0.02737 0.02149 -0.1187 0.9513 0.0549 -5.750 -0.1453 0.02428 0.01782 -0.1230 0.9487 0.0569 -5.500 -0.1045 0.02223 0.01564 -0.1265 0.9466 0.0595 -5.250 -0.0711 0.02091 0.01415 -0.1279 0.9404 0.0615 -5.000 -0.0317 0.01981 0.01283 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0.8082 0.7021 0.000 0.6389 0.01166 0.00571 -0.1496 0.7994 0.7190 0.250 0.6662 0.01168 0.00572 -0.1490 0.7910 0.7325 0.500 0.6922 0.01173 0.00579 -0.1484 0.7815 0.7453 0.750 0.7201 0.01175 0.00578 -0.1480 0.7735 0.7584 1.000 0.7456 0.01180 0.00586 -0.1473 0.7633 0.7714 1.250 0.7730 0.01183 0.00587 -0.1468 0.7547 0.7844 1.500 0.7993 0.01186 0.00591 -0.1462 0.7445 0.7971 1.750 0.8247 0.01188 0.00597 -0.1454 0.7343 0.8091 2.000 0.8508 0.01186 0.00593 -0.1447 0.7235 0.8220 2.250 0.8757 0.01181 0.00587 -0.1436 0.7100 0.8356 2.500 0.8995 0.01177 0.00587 -0.1424 0.6957 0.8501 2.750 0.9230 0.01175 0.00589 -0.1412 0.6827 0.8664 3.000 0.9457 0.01174 0.00591 -0.1398 0.6705 0.8860 3.250 0.9665 0.01169 0.00588 -0.1380 0.6585 0.9139 3.500 0.9913 0.01160 0.00580 -0.1371 0.6458 1.0000 3.750 1.0229 0.01176 0.00594 -0.1380 0.6307 1.0000 4.000 1.0528 0.01194 0.00606 -0.1385 0.6146 1.0000 4.250 1.0811 0.01212 0.00621 -0.1386 0.5963 1.0000 4.500 1.1082 0.01230 0.00637 -0.1384 0.5766 1.0000 4.750 1.1348 0.01252 0.00654 -0.1381 0.5570 1.0000 5.000 1.1606 0.01277 0.00672 -0.1376 0.5364 1.0000 5.250 1.1854 0.01304 0.00695 -0.1370 0.5127 1.0000 5.500 1.2093 0.01338 0.00718 -0.1362 0.4876 1.0000 5.750 1.2325 0.01377 0.00749 -0.1353 0.4604 1.0000 6.000 1.2552 0.01422 0.00785 -0.1344 0.4328 1.0000 6.250 1.2773 0.01472 0.00826 -0.1334 0.4056 1.0000 6.500 1.2988 0.01526 0.00871 -0.1323 0.3774 1.0000 6.750 1.3194 0.01584 0.00921 -0.1311 0.3442 1.0000 7.000 1.3381 0.01655 0.00977 -0.1297 0.3050 1.0000 7.250 1.3547 0.01743 0.01044 -0.1280 0.2631 1.0000 7.500 1.3694 0.01849 0.01126 -0.1262 0.2240 1.0000 7.750 1.3835 0.01962 0.01221 -0.1242 0.1862 1.0000 8.000 1.3952 0.02093 0.01328 -0.1220 0.1486 1.0000 8.250 1.4056 0.02231 0.01445 -0.1195 0.1187 1.0000 8.500 1.4144 0.02369 0.01569 -0.1168 0.1011 1.0000 8.750 1.4216 0.02503 0.01701 -0.1138 0.0907 1.0000 9.000 1.4248 0.02669 0.01858 -0.1105 0.0839 1.0000 9.250 1.4359 0.02784 0.01985 -0.1082 0.0787 1.0000 9.500 1.4433 0.02931 0.02132 -0.1057 0.0744 1.0000 9.750 1.4505 0.03105 0.02308 -0.1033 0.0708 1.0000 10.000 1.4623 0.03234 0.02449 -0.1015 0.0676 1.0000 10.250 1.4729 0.03377 0.02598 -0.0997 0.0646 1.0000 10.500 1.4826 0.03559 0.02776 -0.0980 0.0617 1.0000 10.750 1.4956 0.03730 0.02956 -0.0965 0.0594 1.0000 11.000 1.5070 0.03876 0.03118 -0.0950 0.0569 1.0000 11.250 1.5176 0.04033 0.03283 -0.0936 0.0546 1.0000 11.500 1.5285 0.04205 0.03456 -0.0924 0.0524 1.0000 11.750 1.5440 0.04426 0.03684 -0.0914 0.0500 1.0000 12.000 1.5516 0.04605 0.03884 -0.0899 0.0483 1.0000 12.250 1.5594 0.04800 0.04095 -0.0886 0.0464 1.0000 12.500 1.5673 0.04999 0.04303 -0.0874 0.0447 1.0000 12.750 1.5789 0.05212 0.04513 -0.0866 0.0428 1.0000 13.000 1.5866 0.05504 0.04827 -0.0855 0.0412 1.0000 13.250 1.5868 0.05771 0.05121 -0.0843 0.0400 1.0000 13.500 1.5884 0.06056 0.05427 -0.0833 0.0387 1.0000 13.750 1.5895 0.06351 0.05739 -0.0826 0.0376 1.0000 14.000 1.5909 0.06640 0.06040 -0.0820 0.0365 1.0000 14.250 1.5969 0.06926 0.06329 -0.0816 0.0353 1.0000 14.500 1.5932 0.07408 0.06833 -0.0812 0.0343 1.0000 14.750 1.5796 0.07854 0.07309 -0.0814 0.0338 1.0000 15.000 1.5656 0.08355 0.07840 -0.0820 0.0333 1.0000 15.250 1.5505 0.08902 0.08416 -0.0832 0.0329 1.0000 15.500 1.5342 0.09497 0.09038 -0.0850 0.0324 1.0000 15.750 1.5170 0.10146 0.09713 -0.0875 0.0321 1.0000 16.000 1.4977 0.10861 0.10455 -0.0907 0.0320 1.0000 16.250 1.4750 0.11687 0.11308 -0.0951 0.0320 1.0000 16.500 1.4503 0.12606 0.12254 -0.1007 0.0320 1.0000 16.750 1.4208 0.13697 0.13371 -0.1079 0.0322 1.0000 17.000 1.3867 0.14999 0.14699 -0.1173 0.0327 1.0000 17.250 1.3465 0.16605 0.16327 -0.1292 0.0336 1.0000 17.500 1.2979 0.18754 0.18490 -0.1446 0.0348 1.0000