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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.250 -0.7557 0.07002 0.06797 -0.0460 1.0000 0.0024 -14.000 -0.7858 0.06066 0.05844 -0.0524 1.0000 0.0024 -13.750 -0.8124 0.05320 0.05080 -0.0574 1.0000 0.0024 -13.500 -0.8237 0.04843 0.04591 -0.0604 1.0000 0.0024 -13.250 -0.8429 0.04287 0.04015 -0.0637 1.0000 0.0024 -13.000 -0.8480 0.03928 0.03645 -0.0657 1.0000 0.0024 -12.750 -0.8539 0.03569 0.03272 -0.0676 1.0000 0.0024 -12.500 -0.8538 0.03296 0.02988 -0.0689 1.0000 0.0024 -12.250 -0.8622 0.02967 0.02643 -0.0700 1.0000 0.0024 -12.000 -0.8635 0.02729 0.02394 -0.0708 1.0000 0.0024 -11.750 -0.8321 0.02454 0.02095 -0.0768 0.9616 0.0024 -11.500 -0.7353 0.02138 0.01726 -0.0953 0.8834 0.0025 -11.250 -0.7244 0.02062 0.01611 -0.0938 0.8047 0.0025 -11.000 -0.7120 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8.500 1.2871 0.01816 0.01067 -0.0791 0.0028 0.5944 8.750 1.2993 0.01870 0.01128 -0.0768 0.0027 0.6029 9.000 1.3069 0.01933 0.01200 -0.0739 0.0025 0.6137 9.250 1.3132 0.02006 0.01283 -0.0709 0.0024 0.6270 9.500 1.3150 0.02105 0.01394 -0.0677 0.0023 0.6435 9.750 1.3182 0.02210 0.01513 -0.0652 0.0023 0.6692 10.000 1.3186 0.02345 0.01668 -0.0628 0.0023 0.7147 10.250 1.3203 0.02506 0.01891 -0.0618 0.0022 1.0000 10.500 1.3219 0.02716 0.02109 -0.0609 0.0022 1.0000 10.750 1.3214 0.02968 0.02369 -0.0602 0.0021 1.0000 11.000 1.3210 0.03234 0.02644 -0.0598 0.0021 1.0000 11.250 1.3147 0.03567 0.02988 -0.0594 0.0021 1.0000 11.500 1.3170 0.03817 0.03243 -0.0591 0.0021 1.0000 11.750 1.3113 0.04151 0.03586 -0.0588 0.0021 1.0000 12.000 1.3071 0.04474 0.03917 -0.0587 0.0021 1.0000 12.250 1.3010 0.04818 0.04269 -0.0585 0.0021 1.0000 12.500 1.2984 0.05128 0.04586 -0.0584 0.0021 1.0000 12.750 1.2946 0.05457 0.04923 -0.0584 0.0021 1.0000 13.000 1.2924 0.05781 0.05254 -0.0586 0.0021 1.0000 13.250 1.2895 0.06125 0.05605 -0.0588 0.0021 1.0000 13.500 1.2905 0.06424 0.05910 -0.0591 0.0021 1.0000 13.750 1.2875 0.06783 0.06277 -0.0594 0.0021 1.0000 14.000 1.2876 0.07107 0.06608 -0.0598 0.0021 1.0000 14.250 1.2865 0.07450 0.06959 -0.0603 0.0022 1.0000 14.500 1.2876 0.07771 0.07287 -0.0608 0.0022 1.0000 14.750 1.2855 0.08139 0.07664 -0.0613 0.0023 1.0000 15.000 1.2876 0.08452 0.07985 -0.0619 0.0023 1.0000