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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -0.7333 0.05711 0.05431 -0.0588 1.0000 0.0024 -13.000 -0.7567 0.05056 0.04757 -0.0630 1.0000 0.0023 -12.750 -0.7744 0.04520 0.04202 -0.0661 1.0000 0.0023 -12.500 -0.7815 0.04146 0.03814 -0.0681 1.0000 0.0023 -12.250 -0.7323 0.03383 0.02994 -0.0871 0.9083 0.0025 -12.000 -0.7056 0.03104 0.02651 -0.0935 0.7963 0.0025 -11.750 -0.7072 0.02912 0.02428 -0.0928 0.7530 0.0026 -11.500 -0.7095 0.02753 0.02243 -0.0916 0.7220 0.0026 -11.250 -0.7025 0.02619 0.02086 -0.0908 0.6974 0.0026 -11.000 -0.6917 0.02496 0.01937 -0.0900 0.6770 0.0027 -10.750 -0.6776 0.02386 0.01808 -0.0893 0.6610 0.0028 -10.500 -0.6611 0.02289 0.01694 -0.0887 0.6452 0.0028 -10.250 -0.6440 0.02186 0.01573 -0.0881 0.6298 0.0031 -10.000 -0.6259 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0.00979 0.00230 -0.0902 0.4406 0.4626 -0.250 0.4165 0.00984 0.00232 -0.0904 0.4375 0.4707 0.000 0.4448 0.00990 0.00233 -0.0904 0.4337 0.4748 0.250 0.4734 0.00992 0.00234 -0.0906 0.4300 0.4780 0.500 0.5019 0.00996 0.00235 -0.0907 0.4258 0.4809 0.750 0.5302 0.01002 0.00236 -0.0908 0.4224 0.4834 1.000 0.5584 0.01007 0.00240 -0.0909 0.4191 0.4861 1.250 0.5869 0.01011 0.00245 -0.0910 0.4165 0.4890 1.500 0.6152 0.01016 0.00249 -0.0912 0.4135 0.4917 1.750 0.6435 0.01022 0.00255 -0.0913 0.4107 0.4943 2.000 0.6716 0.01029 0.00260 -0.0914 0.4083 0.4965 2.250 0.6995 0.01037 0.00266 -0.0915 0.4058 0.4984 2.500 0.7278 0.01041 0.00274 -0.0916 0.4018 0.5007 2.750 0.7557 0.01047 0.00281 -0.0917 0.3948 0.5044 3.000 0.7835 0.01055 0.00288 -0.0917 0.3874 0.5084 3.250 0.8113 0.01063 0.00296 -0.0918 0.3793 0.5119 3.500 0.8390 0.01071 0.00306 -0.0919 0.3739 0.5146 3.750 0.8665 0.01080 0.00316 -0.0919 0.3665 0.5168 4.000 0.8938 0.01091 0.00327 -0.0919 0.3602 0.5195 4.250 0.9209 0.01103 0.00341 -0.0919 0.3534 0.5224 4.500 0.9478 0.01118 0.00355 -0.0918 0.3474 0.5262 4.750 0.9749 0.01130 0.00371 -0.0918 0.3410 0.5296 5.000 1.0013 0.01148 0.00389 -0.0917 0.3332 0.5330 5.250 1.0263 0.01177 0.00413 -0.0914 0.3065 0.5362 5.500 1.0341 0.01367 0.00539 -0.0890 0.1874 0.5386 5.750 1.0483 0.01489 0.00630 -0.0873 0.1261 0.5410 6.000 1.0667 0.01566 0.00695 -0.0862 0.0902 0.5435 6.250 1.0886 0.01610 0.00738 -0.0855 0.0788 0.5465 6.500 1.1078 0.01673 0.00795 -0.0844 0.0556 0.5498 6.750 1.1296 0.01713 0.00837 -0.0837 0.0485 0.5534 7.000 1.1473 0.01778 0.00901 -0.0825 0.0304 0.5567 7.250 1.1670 0.01823 0.00951 -0.0815 0.0274 0.5606 7.500 1.1856 0.01873 0.01005 -0.0803 0.0232 0.5649 7.750 1.2048 0.01915 0.01053 -0.0792 0.0211 0.5698 8.000 1.2130 0.02007 0.01142 -0.0767 0.0047 0.5744 8.250 1.2221 0.02070 0.01212 -0.0740 0.0040 0.5800 8.750 1.2373 0.02225 0.01385 -0.0689 0.0030 0.5924 9.000 1.2424 0.02327 0.01496 -0.0665 0.0027 0.5996 9.250 1.2462 0.02450 0.01631 -0.0644 0.0026 0.6077 9.500 1.2486 0.02603 0.01795 -0.0627 0.0024 0.6171 9.750 1.2508 0.02781 0.01986 -0.0614 0.0024 0.6280 10.000 1.2532 0.02979 0.02197 -0.0605 0.0023 0.6414 10.250 1.2533 0.03215 0.02448 -0.0597 0.0022 0.6584 10.500 1.2543 0.03452 0.02701 -0.0592 0.0022 0.6833 10.750 1.2541 0.03696 0.02967 -0.0586 0.0021 0.7282 11.250 1.2585 0.04260 0.03592 -0.0599 0.0019 1.0000 11.500 1.2601 0.04522 0.03863 -0.0597 0.0020 1.0000 11.750 1.2563 0.04843 0.04193 -0.0596 0.0019 1.0000 12.000 1.2521 0.05171 0.04531 -0.0595 0.0018 1.0000 12.250 1.2485 0.05498 0.04865 -0.0595 0.0018 1.0000 12.500 1.2489 0.05789 0.05164 -0.0596 0.0018 1.0000 12.750 1.2492 0.06092 0.05474 -0.0598 0.0017 1.0000 13.000 1.2505 0.06388 0.05777 -0.0601 0.0017 1.0000 13.250 1.2506 0.06706 0.06102 -0.0605 0.0017 1.0000 13.500 1.2523 0.07008 0.06411 -0.0608 0.0017 1.0000 13.750 1.2524 0.07340 0.06751 -0.0613 0.0016 1.0000 14.000 1.2536 0.07659 0.07077 -0.0618 0.0016 1.0000 14.250 1.2541 0.07996 0.07422 -0.0625 0.0016 1.0000 14.500 1.2556 0.08323 0.07756 -0.0631 0.0016 1.0000 14.750 1.2554 0.08680 0.08121 -0.0639 0.0015 1.0000 15.000 1.2572 0.09011 0.08459 -0.0646 0.0015 1.0000