XFOIL Version 6.96 Calculated polar for: FX 66-17AII-182 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.500 -0.3138 0.09250 0.08831 -0.0859 0.7978 0.0158 -13.250 -0.3520 0.07867 0.07435 -0.0944 0.7914 0.0155 -13.000 -0.3781 0.06950 0.06497 -0.1011 0.7758 0.0152 -12.750 -0.4088 0.06154 0.05671 -0.1066 0.7616 0.0152 -12.500 -0.4289 0.05635 0.05126 -0.1094 0.7460 0.0151 -12.250 -0.4487 0.05185 0.04649 -0.1110 0.7329 0.0152 -12.000 -0.4652 0.04804 0.04239 -0.1118 0.7210 0.0152 -11.750 -0.4802 0.04456 0.03861 -0.1119 0.7103 0.0153 -11.500 -0.4900 0.04168 0.03545 -0.1115 0.7009 0.0154 -11.250 -0.4990 0.03899 0.03243 -0.1106 0.6925 0.0156 -11.000 -0.5057 0.03661 0.02971 -0.1093 0.6846 0.0159 -10.750 -0.5067 0.03461 0.02744 -0.1077 0.6773 0.0161 -10.500 -0.5006 0.03306 0.02575 -0.1064 0.6705 0.0163 -10.250 -0.4936 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0.3746 0.01515 0.00648 -0.0796 0.5456 0.6305 0.000 0.4016 0.01519 0.00653 -0.0796 0.5433 0.6329 0.250 0.4287 0.01525 0.00657 -0.0796 0.5411 0.6355 0.500 0.4561 0.01532 0.00660 -0.0797 0.5392 0.6382 0.750 0.4836 0.01539 0.00663 -0.0799 0.5374 0.6413 1.000 0.5113 0.01547 0.00664 -0.0801 0.5357 0.6447 1.250 0.5392 0.01554 0.00668 -0.0803 0.5341 0.6471 1.500 0.5657 0.01564 0.00680 -0.0802 0.5321 0.6496 1.750 0.5916 0.01574 0.00696 -0.0801 0.5297 0.6526 2.000 0.6179 0.01585 0.00709 -0.0800 0.5275 0.6559 2.250 0.6446 0.01596 0.00720 -0.0801 0.5255 0.6589 2.500 0.6715 0.01607 0.00730 -0.0801 0.5236 0.6614 2.750 0.6985 0.01615 0.00742 -0.0802 0.5219 0.6635 3.000 0.7259 0.01624 0.00751 -0.0803 0.5201 0.6660 3.250 0.7536 0.01635 0.00760 -0.0805 0.5185 0.6689 3.500 0.7788 0.01651 0.00784 -0.0803 0.5163 0.6717 3.750 0.8035 0.01668 0.00808 -0.0801 0.5140 0.6745 4.000 0.8288 0.01684 0.00829 -0.0799 0.5117 0.6772 4.250 0.8543 0.01696 0.00850 -0.0797 0.5094 0.6797 4.500 0.8804 0.01708 0.00867 -0.0797 0.5074 0.6827 4.750 0.9071 0.01720 0.00882 -0.0797 0.5056 0.6859 5.000 0.9343 0.01733 0.00897 -0.0799 0.5040 0.6892 5.250 0.9603 0.01751 0.00919 -0.0798 0.5020 0.6924 5.500 0.9820 0.01774 0.00959 -0.0791 0.4993 0.6952 5.750 1.0052 0.01797 0.00993 -0.0786 0.4969 0.6983 6.000 1.0294 0.01818 0.01025 -0.0783 0.4947 0.7021 6.250 1.0545 0.01837 0.01051 -0.0781 0.4927 0.7064 6.500 1.0803 0.01852 0.01074 -0.0780 0.4908 0.7102 6.750 1.1069 0.01865 0.01095 -0.0781 0.4890 0.7142 7.000 1.1326 0.01883 0.01122 -0.0780 0.4872 0.7187 7.250 1.1508 0.01922 0.01178 -0.0768 0.4842 0.7235 7.500 1.1708 0.01953 0.01227 -0.0758 0.4816 0.7280 7.750 1.1924 0.01971 0.01258 -0.0750 0.4786 0.7336 8.000 1.2173 0.01974 0.01269 -0.0747 0.4756 0.7400 8.250 1.2423 0.01969 0.01273 -0.0744 0.4716 0.7469 8.750 1.2787 0.01979 0.01312 -0.0716 0.4600 0.7647 9.000 1.2954 0.01993 0.01342 -0.0700 0.4544 0.7763 9.250 1.3092 0.02003 0.01369 -0.0678 0.4473 0.7923 9.750 1.3495 0.02003 0.01418 -0.0666 0.4240 0.9315 10.000 1.3478 0.02047 0.01461 -0.0622 0.4091 1.0000 10.250 1.3487 0.02119 0.01532 -0.0588 0.3911 1.0000 10.500 1.3465 0.02228 0.01632 -0.0556 0.3707 1.0000 10.750 1.3459 0.02366 0.01770 -0.0531 0.3539 1.0000 11.000 1.3400 0.02557 0.01957 -0.0506 0.3325 1.0000 11.250 1.3285 0.02816 0.02207 -0.0483 0.3096 1.0000 11.500 1.3111 0.03151 0.02531 -0.0461 0.2811 1.0000 11.750 1.2921 0.03524 0.02893 -0.0443 0.2571 1.0000 12.000 1.2708 0.03936 0.03293 -0.0427 0.2329 1.0000 12.250 1.2489 0.04366 0.03712 -0.0413 0.2084 1.0000 12.500 1.2319 0.04771 0.04108 -0.0403 0.1861 1.0000 12.750 1.2109 0.05234 0.04555 -0.0394 0.1589 1.0000 13.000 1.1994 0.05615 0.04928 -0.0388 0.1392 1.0000 13.250 1.1857 0.06031 0.05330 -0.0384 0.1151 1.0000 13.500 1.1770 0.06404 0.05693 -0.0381 0.0958 1.0000 13.750 1.1683 0.06782 0.06061 -0.0379 0.0769 1.0000 14.000 1.1629 0.07133 0.06404 -0.0378 0.0615 1.0000 14.250 1.1594 0.07469 0.06735 -0.0378 0.0493 1.0000 14.500 1.1581 0.07783 0.07048 -0.0379 0.0409 1.0000 14.750 1.1564 0.08107 0.07371 -0.0380 0.0340 1.0000 15.000 1.1562 0.08419 0.07683 -0.0382 0.0290 1.0000 15.250 1.1572 0.08721 0.07990 -0.0384 0.0247 1.0000 15.750 1.1604 0.09317 0.08599 -0.0390 0.0207 1.0000 16.000 1.1626 0.09612 0.08900 -0.0394 0.0192 1.0000 16.250 1.1630 0.09932 0.09224 -0.0399 0.0179 1.0000 16.500 1.1640 0.10249 0.09548 -0.0404 0.0171 1.0000 16.750 1.1656 0.10561 0.09869 -0.0410 0.0163 1.0000 17.000 1.1666 0.10880 0.10196 -0.0417 0.0155 1.0000 17.250 1.1673 0.11207 0.10530 -0.0424 0.0150 1.0000 17.500 1.1666 0.11558 0.10887 -0.0433 0.0145 1.0000