XFOIL Version 6.96 Calculated polar for: FX S 02/1-158 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3717 0.09215 0.08777 -0.0472 1.0000 0.0314 -10.500 -0.3840 0.08436 0.08003 -0.0518 1.0000 0.0314 -10.250 -0.4001 0.07729 0.07299 -0.0564 1.0000 0.0313 -10.000 -0.4192 0.07100 0.06670 -0.0607 1.0000 0.0312 -9.750 -0.4380 0.06582 0.06151 -0.0640 1.0000 0.0310 -9.250 -0.4498 0.05204 0.04677 -0.0845 0.8336 0.0323 -8.750 -0.4312 0.04680 0.04101 -0.0867 0.7666 0.0351 -8.500 -0.4256 0.04370 0.03748 -0.0872 0.7437 0.0357 -8.250 -0.4153 0.04092 0.03424 -0.0873 0.7250 0.0365 -8.000 -0.4009 0.03877 0.03166 -0.0874 0.7085 0.0385 -7.750 -0.3843 0.03649 0.02885 -0.0874 0.6938 0.0398 -7.500 -0.3650 0.03421 0.02612 -0.0873 0.6812 0.0402 -7.250 -0.3433 0.03226 0.02375 -0.0871 0.6699 0.0407 -7.000 -0.3197 0.03054 0.02166 -0.0869 0.6597 0.0412 -6.750 -0.2952 0.02908 0.01989 -0.0867 0.6505 0.0417 -6.500 -0.2701 0.02780 0.01835 -0.0864 0.6412 0.0423 -6.250 -0.2452 0.02662 0.01697 -0.0861 0.6335 0.0436 -6.000 -0.2210 0.02549 0.01581 -0.0859 0.6258 0.0455 -5.750 -0.1962 0.02463 0.01482 -0.0855 0.6193 0.0470 -5.500 -0.1716 0.02382 0.01393 -0.0849 0.6123 0.0478 -5.250 -0.1473 0.02312 0.01313 -0.0843 0.6067 0.0489 -5.000 -0.1230 0.02250 0.01246 -0.0838 0.6003 0.0502 -4.750 -0.0984 0.02196 0.01180 -0.0835 0.5950 0.0518 -4.500 -0.0730 0.02147 0.01115 -0.0833 0.5904 0.0539 -4.250 -0.0474 0.02089 0.01046 -0.0834 0.5853 0.0569 -4.000 -0.0209 0.02039 0.00979 -0.0837 0.5807 0.0627 -3.750 0.0060 0.01977 0.00907 -0.0840 0.5764 0.0736 -3.500 0.0323 0.01865 0.00828 -0.0850 0.5712 0.1508 -3.250 0.0562 0.01796 0.00874 -0.0853 0.5668 0.4545 -3.000 0.0828 0.01876 0.00941 -0.0844 0.5631 0.5018 -2.750 0.1078 0.01949 0.01017 -0.0830 0.5587 0.5317 -2.500 0.1350 0.01969 0.01022 -0.0826 0.5550 0.5438 -2.250 0.1626 0.01973 0.01010 -0.0825 0.5517 0.5489 -2.000 0.1913 0.01977 0.00987 -0.0829 0.5489 0.5564 -1.750 0.2178 0.01988 0.00998 -0.0825 0.5451 0.5625 -1.500 0.2460 0.01994 0.00989 -0.0827 0.5415 0.5702 -1.250 0.2734 0.01998 0.00983 -0.0826 0.5384 0.5742 -1.000 0.3015 0.02000 0.00972 -0.0828 0.5358 0.5773 -0.750 0.3299 0.02003 0.00964 -0.0831 0.5332 0.5802 -0.500 0.3581 0.02008 0.00962 -0.0835 0.5301 0.5835 -0.250 0.3864 0.02014 0.00960 -0.0839 0.5272 0.5861 0.000 0.4141 0.02021 0.00962 -0.0841 0.5247 0.5881 0.250 0.4422 0.02028 0.00962 -0.0843 0.5224 0.5903 0.500 0.4705 0.02038 0.00963 -0.0845 0.5205 0.5931 0.750 0.4980 0.02053 0.00979 -0.0848 0.5178 0.5963 1.000 0.5257 0.02070 0.00995 -0.0851 0.5151 0.5996 1.250 0.5530 0.02086 0.01012 -0.0853 0.5126 0.6020 1.500 0.5804 0.02101 0.01027 -0.0854 0.5102 0.6045 1.750 0.6081 0.02115 0.01039 -0.0856 0.5080 0.6075 2.000 0.6363 0.02131 0.01050 -0.0858 0.5061 0.6111 2.250 0.6630 0.02158 0.01082 -0.0860 0.5034 0.6149 2.500 0.6889 0.02185 0.01119 -0.0860 0.5008 0.6177 2.750 0.7153 0.02211 0.01154 -0.0861 0.4985 0.6209 3.000 0.7423 0.02238 0.01184 -0.0862 0.4964 0.6245 3.250 0.7696 0.02264 0.01212 -0.0864 0.4945 0.6289 3.500 0.7968 0.02288 0.01240 -0.0865 0.4929 0.6326 3.750 0.8237 0.02315 0.01274 -0.0865 0.4910 0.6369 4.000 0.8476 0.02361 0.01336 -0.0864 0.4873 0.6416 4.250 0.8730 0.02393 0.01379 -0.0863 0.4839 0.6460 4.500 0.8995 0.02419 0.01412 -0.0863 0.4813 0.6506 4.750 0.9270 0.02443 0.01443 -0.0865 0.4791 0.6562 5.000 0.9548 0.02467 0.01472 -0.0866 0.4774 0.6621 5.250 0.9763 0.02530 0.01559 -0.0862 0.4740 0.6687 5.500 0.9990 0.02587 0.01635 -0.0859 0.4709 0.6761 5.750 1.0234 0.02629 0.01695 -0.0857 0.4681 0.6844 6.000 1.0493 0.02657 0.01737 -0.0856 0.4657 0.6936 6.250 1.0765 0.02680 0.01770 -0.0856 0.4637 0.7046 6.500 1.0969 0.02739 0.01854 -0.0850 0.4600 0.7174 6.750 1.1164 0.02778 0.01920 -0.0841 0.4544 0.7343 7.000 1.1454 0.02724 0.01880 -0.0837 0.4496 0.7602 7.250 1.1596 0.02746 0.01942 -0.0817 0.4426 0.8123 7.500 1.1871 0.02680 0.01890 -0.0812 0.4360 1.0000 7.750 1.2072 0.02719 0.01944 -0.0805 0.4295 1.0000 8.000 1.2301 0.02742 0.01978 -0.0800 0.4241 1.0000 8.250 1.2601 0.02715 0.01953 -0.0800 0.4200 1.0000 8.500 1.2716 0.02807 0.02076 -0.0785 0.4128 1.0000 8.750 1.3006 0.02747 0.02017 -0.0781 0.4054 1.0000 9.000 1.3097 0.02804 0.02097 -0.0760 0.3935 1.0000 9.250 1.3185 0.02859 0.02171 -0.0739 0.3804 1.0000 9.500 1.3255 0.02926 0.02254 -0.0716 0.3668 1.0000 9.750 1.3300 0.02984 0.02320 -0.0688 0.3520 1.0000 10.000 1.3270 0.03115 0.02461 -0.0659 0.3388 1.0000 10.250 1.3089 0.03399 0.02759 -0.0631 0.3250 1.0000 10.500 1.2772 0.03916 0.03291 -0.0619 0.3178 1.0000 10.750 1.2365 0.04662 0.04055 -0.0623 0.3171 1.0000 11.000 1.2134 0.05218 0.04619 -0.0627 0.3040 1.0000 11.250 1.2536 0.04800 0.04108 -0.0598 0.2215 1.0000 11.500 1.2328 0.05298 0.04594 -0.0598 0.1903 1.0000 11.750 1.2138 0.05789 0.05074 -0.0599 0.1756 1.0000 12.000 1.1957 0.06283 0.05558 -0.0602 0.1450 1.0000 12.250 1.1750 0.06822 0.06077 -0.0608 0.1297 1.0000 12.500 1.1674 0.07230 0.06483 -0.0613 0.1033 1.0000 12.750 1.1527 0.07739 0.06974 -0.0621 0.0886 1.0000 13.000 1.1495 0.08115 0.07356 -0.0627 0.0677 1.0000 13.250 1.1405 0.08576 0.07801 -0.0636 0.0559 1.0000 13.500 1.1381 0.08955 0.08180 -0.0644 0.0460 1.0000 13.750 1.1336 0.09369 0.08584 -0.0653 0.0348 1.0000 14.000 1.1320 0.09751 0.08966 -0.0661 0.0289 1.0000