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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.750 -0.7830 0.07273 0.07055 -0.0451 1.0000 0.0012 -14.500 -0.8349 0.05986 0.05743 -0.0539 1.0000 0.0012 -14.250 -0.8556 0.05349 0.05091 -0.0580 1.0000 0.0012 -14.000 -0.8670 0.04787 0.04513 -0.0626 0.9990 0.0012 -13.750 -0.7996 0.03864 0.03528 -0.0889 0.8859 0.0012 -13.500 -0.7883 0.03602 0.03209 -0.0926 0.7699 0.0012 -13.250 -0.7933 0.03313 0.02895 -0.0935 0.7344 0.0012 -13.000 -0.7904 0.03117 0.02680 -0.0938 0.7049 0.0012 -12.750 -0.7888 0.02914 0.02459 -0.0939 0.6814 0.0012 -12.500 -0.7847 0.02745 0.02275 -0.0938 0.6648 0.0012 -12.250 -0.7861 0.02555 0.02069 -0.0932 0.6504 0.0013 -12.000 -0.7841 0.02420 0.01921 -0.0923 0.6345 0.0013 -11.750 -0.7730 0.02309 0.01794 -0.0915 0.6193 0.0013 -11.250 -0.7416 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-1.750 0.2553 0.00936 0.00185 -0.0905 0.4120 0.0642 -1.500 0.2837 0.00935 0.00180 -0.0906 0.4067 0.0686 -1.250 0.3123 0.00929 0.00175 -0.0908 0.4027 0.0773 -1.000 0.3409 0.00921 0.00170 -0.0910 0.3991 0.1020 -0.750 0.3695 0.00915 0.00166 -0.0912 0.3958 0.1146 -0.500 0.3979 0.00904 0.00161 -0.0914 0.3925 0.1523 -0.250 0.4264 0.00891 0.00157 -0.0917 0.3899 0.1951 0.000 0.4547 0.00865 0.00149 -0.0920 0.3866 0.2645 0.250 0.4823 0.00816 0.00143 -0.0924 0.3819 0.4116 0.500 0.5106 0.00819 0.00149 -0.0925 0.3759 0.4362 0.750 0.5391 0.00825 0.00152 -0.0926 0.3704 0.4411 1.000 0.5671 0.00834 0.00157 -0.0927 0.3614 0.4458 1.250 0.5945 0.00851 0.00166 -0.0927 0.3465 0.4507 1.500 0.6197 0.00891 0.00185 -0.0924 0.3036 0.4538 1.750 0.6410 0.00974 0.00232 -0.0916 0.2286 0.4569 2.000 0.6649 0.01028 0.00267 -0.0911 0.1806 0.4599 2.250 0.6919 0.01048 0.00282 -0.0911 0.1708 0.4626 2.500 0.7193 0.01062 0.00294 -0.0911 0.1650 0.4648 2.750 0.7450 0.01095 0.00318 -0.0909 0.1385 0.4673 3.000 0.7714 0.01119 0.00336 -0.0907 0.1270 0.4696 3.250 0.7980 0.01139 0.00355 -0.0906 0.1186 0.4729 3.500 0.8251 0.01154 0.00370 -0.0906 0.1149 0.4759 3.750 0.8504 0.01187 0.00396 -0.0903 0.0932 0.4786 4.000 0.8772 0.01204 0.00412 -0.0903 0.0913 0.4810 4.250 0.9037 0.01223 0.00430 -0.0902 0.0888 0.4832 4.500 0.9301 0.01240 0.00450 -0.0901 0.0864 0.4877 4.750 0.9562 0.01260 0.00472 -0.0899 0.0818 0.4925 5.000 0.9796 0.01305 0.00508 -0.0894 0.0571 0.4968 5.250 1.0049 0.01330 0.00533 -0.0891 0.0512 0.4995 5.500 1.0301 0.01355 0.00561 -0.0889 0.0405 0.5023 5.750 1.0528 0.01399 0.00600 -0.0882 0.0280 0.5051 6.000 1.0773 0.01428 0.00629 -0.0879 0.0239 0.5077 6.250 1.1018 0.01454 0.00657 -0.0875 0.0219 0.5102 6.750 1.1442 0.01550 0.00752 -0.0858 0.0025 0.5168 7.000 1.1665 0.01587 0.00793 -0.0851 0.0021 0.5211 7.250 1.1884 0.01624 0.00834 -0.0844 0.0018 0.5251 7.500 1.2096 0.01662 0.00876 -0.0835 0.0017 0.5282 7.750 1.2299 0.01702 0.00921 -0.0826 0.0017 0.5314 8.000 1.2493 0.01746 0.00969 -0.0815 0.0016 0.5350 8.250 1.2673 0.01792 0.01022 -0.0802 0.0015 0.5386 8.750 1.2951 0.01894 0.01135 -0.0763 0.0014 0.5464 9.000 1.3042 0.01954 0.01202 -0.0736 0.0013 0.5513 9.250 1.3116 0.02026 0.01280 -0.0708 0.0013 0.5560 9.500 1.3168 0.02112 0.01374 -0.0681 0.0012 0.5609 9.750 1.3204 0.02220 0.01490 -0.0656 0.0012 0.5664 10.250 1.3228 0.02527 0.01814 -0.0616 0.0011 0.5779 10.500 1.3240 0.02720 0.02016 -0.0603 0.0011 0.5844 10.750 1.3244 0.02941 0.02249 -0.0594 0.0011 0.5921 11.250 1.3156 0.03520 0.02851 -0.0579 0.0009 0.6105 11.500 1.3208 0.03725 0.03064 -0.0576 0.0010 0.6232 11.750 1.3118 0.04078 0.03430 -0.0571 0.0009 0.6359 12.000 1.3031 0.04435 0.03801 -0.0567 0.0009 0.6518 12.250 1.2899 0.04844 0.04226 -0.0565 0.0008 0.6724 12.500 1.2878 0.05132 0.04532 -0.0563 0.0008 0.7167 13.000 1.2964 0.05722 0.05187 -0.0588 0.0008 1.0000 13.250 1.2961 0.06032 0.05504 -0.0590 0.0008 1.0000 13.500 1.2954 0.06350 0.05828 -0.0593 0.0008 1.0000 13.750 1.2958 0.06664 0.06148 -0.0596 0.0008 1.0000 14.000 1.2964 0.06978 0.06469 -0.0600 0.0008 1.0000 14.250 1.2970 0.07301 0.06798 -0.0605 0.0008 1.0000 14.500 1.2975 0.07627 0.07131 -0.0611 0.0008 1.0000 14.750 1.2981 0.07962 0.07474 -0.0617 0.0007 1.0000 15.000 1.2990 0.08295 0.07813 -0.0624 0.0008 1.0000 15.250 1.2989 0.08648 0.08172 -0.0631 0.0008 1.0000