XFOIL Version 6.96 Calculated polar for: FX 66-S-196 V1 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -0.4467 0.07790 0.07374 -0.0974 0.9010 0.0150 -14.250 -0.4702 0.06808 0.06351 -0.1064 0.8824 0.0149 -14.000 -0.4791 0.06218 0.05732 -0.1117 0.8622 0.0150 -13.750 -0.4866 0.05755 0.05242 -0.1153 0.8443 0.0150 -13.500 -0.4888 0.05410 0.04878 -0.1177 0.8274 0.0153 -13.250 -0.4961 0.05040 0.04480 -0.1194 0.8129 0.0152 -13.000 -0.4993 0.04762 0.04181 -0.1201 0.7989 0.0154 -12.750 -0.4998 0.04535 0.03936 -0.1205 0.7855 0.0156 -12.500 -0.5006 0.04301 0.03683 -0.1206 0.7730 0.0158 -12.250 -0.4989 0.04103 0.03465 -0.1205 0.7613 0.0161 -12.000 -0.4960 0.03923 0.03265 -0.1202 0.7507 0.0165 -11.750 -0.4925 0.03751 0.03073 -0.1197 0.7402 0.0170 -11.500 -0.4870 0.03584 0.02884 -0.1191 0.7305 0.0174 -11.250 -0.4804 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-1.250 0.3281 0.01517 0.00633 -0.0998 0.5641 0.5687 -1.000 0.3559 0.01520 0.00633 -0.1001 0.5622 0.5708 -0.750 0.3837 0.01523 0.00636 -0.1003 0.5604 0.5724 -0.500 0.4115 0.01528 0.00639 -0.1006 0.5587 0.5744 -0.250 0.4395 0.01534 0.00642 -0.1009 0.5571 0.5766 0.000 0.4675 0.01540 0.00645 -0.1012 0.5556 0.5788 0.250 0.4957 0.01546 0.00647 -0.1016 0.5542 0.5810 0.500 0.5240 0.01554 0.00650 -0.1020 0.5529 0.5833 0.750 0.5525 0.01563 0.00653 -0.1024 0.5518 0.5857 1.000 0.5809 0.01573 0.00661 -0.1028 0.5507 0.5875 1.250 0.6081 0.01584 0.00676 -0.1030 0.5494 0.5896 1.500 0.6349 0.01596 0.00694 -0.1032 0.5480 0.5919 1.750 0.6617 0.01609 0.00711 -0.1033 0.5466 0.5945 2.000 0.6886 0.01624 0.00728 -0.1035 0.5451 0.5976 2.250 0.7157 0.01638 0.00744 -0.1037 0.5436 0.6009 2.500 0.7425 0.01651 0.00761 -0.1039 0.5421 0.6036 2.750 0.7695 0.01664 0.00780 -0.1040 0.5408 0.6063 3.000 0.7967 0.01680 0.00799 -0.1043 0.5396 0.6094 3.250 0.8240 0.01696 0.00818 -0.1045 0.5386 0.6129 3.500 0.8516 0.01713 0.00837 -0.1049 0.5376 0.6166 3.750 0.8791 0.01730 0.00859 -0.1051 0.5367 0.6199 4.000 0.9068 0.01747 0.00881 -0.1055 0.5357 0.6235 4.250 0.9329 0.01769 0.00910 -0.1055 0.5345 0.6276 4.500 0.9566 0.01796 0.00948 -0.1052 0.5329 0.6322 4.750 0.9805 0.01822 0.00986 -0.1050 0.5314 0.6363 5.000 1.0044 0.01847 0.01023 -0.1047 0.5297 0.6409 5.250 1.0289 0.01874 0.01061 -0.1045 0.5283 0.6463 5.500 1.0535 0.01901 0.01099 -0.1044 0.5271 0.6516 5.750 1.0781 0.01927 0.01135 -0.1042 0.5258 0.6573 6.000 1.1035 0.01950 0.01168 -0.1042 0.5244 0.6643 6.250 1.1292 0.01972 0.01201 -0.1042 0.5232 0.6711 6.500 1.1551 0.01997 0.01235 -0.1043 0.5221 0.6793 6.750 1.1814 0.02022 0.01272 -0.1044 0.5212 0.6873 7.000 1.2087 0.02048 0.01306 -0.1047 0.5202 0.6967 7.250 1.2242 0.02095 0.01375 -0.1031 0.5180 0.7058 7.500 1.2391 0.02143 0.01442 -0.1015 0.5153 0.7165 7.750 1.2572 0.02180 0.01498 -0.1003 0.5128 0.7287 8.000 1.2775 0.02211 0.01545 -0.0994 0.5107 0.7421 8.250 1.3001 0.02236 0.01585 -0.0989 0.5089 0.7575 8.500 1.3266 0.02247 0.01609 -0.0990 0.5071 0.7760 8.750 1.3580 0.02239 0.01614 -0.0997 0.5052 0.7981 9.000 1.3601 0.02305 0.01707 -0.0959 0.5015 0.8277 9.250 1.3633 0.02350 0.01779 -0.0923 0.4972 0.8764 9.500 1.3975 0.02269 0.01707 -0.0931 0.4914 1.0000 9.750 1.3891 0.02308 0.01755 -0.0876 0.4833 1.0000 10.000 1.3936 0.02280 0.01726 -0.0840 0.4714 1.0000 10.250 1.3893 0.02326 0.01775 -0.0799 0.4583 1.0000 10.500 1.3828 0.02435 0.01888 -0.0763 0.4449 1.0000 10.750 1.3634 0.02691 0.02159 -0.0725 0.4336 1.0000 11.000 1.3433 0.03009 0.02490 -0.0694 0.4217 1.0000 11.250 1.3149 0.03452 0.02946 -0.0666 0.4090 1.0000 11.500 1.3391 0.03394 0.02863 -0.0660 0.3715 1.0000 11.750 1.3302 0.03636 0.03077 -0.0638 0.3338 1.0000 12.000 1.3110 0.03997 0.03417 -0.0615 0.3041 1.0000 12.250 1.2932 0.04379 0.03784 -0.0596 0.2760 1.0000 12.500 1.2749 0.04787 0.04176 -0.0581 0.2505 1.0000 12.750 1.2580 0.05201 0.04576 -0.0568 0.2231 1.0000 13.000 1.2433 0.05611 0.04971 -0.0559 0.1984 1.0000 13.250 1.2300 0.06019 0.05365 -0.0551 0.1710 1.0000 13.500 1.2174 0.06430 0.05759 -0.0545 0.1442 1.0000 13.750 1.2090 0.06805 0.06121 -0.0541 0.1196 1.0000 14.000 1.2008 0.07188 0.06490 -0.0538 0.0954 1.0000 14.250 1.1950 0.07548 0.06836 -0.0537 0.0746 1.0000 14.500 1.1911 0.07893 0.07171 -0.0536 0.0572 1.0000 14.750 1.1892 0.08223 0.07493 -0.0536 0.0451 1.0000 15.250 1.1907 0.08833 0.08102 -0.0538 0.0310 1.0000 15.500 1.1923 0.09135 0.08408 -0.0540 0.0272 1.0000