XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0612 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1290 0.11005 0.10708 -0.0293 1.0000 0.0141 -19.500 -1.1804 0.09663 0.09345 -0.0366 1.0000 0.0140 -19.250 -1.2201 0.08554 0.08217 -0.0428 1.0000 0.0140 -19.000 -1.2492 0.07660 0.07306 -0.0479 1.0000 0.0140 -18.750 -1.2700 0.06932 0.06562 -0.0520 1.0000 0.0140 -18.500 -1.2849 0.06332 0.05949 -0.0553 1.0000 0.0141 -18.250 -1.2949 0.05831 0.05435 -0.0579 1.0000 0.0141 -18.000 -1.3017 0.05401 0.04995 -0.0600 1.0000 0.0142 -17.750 -1.3056 0.05031 0.04615 -0.0616 1.0000 0.0143 -17.500 -1.3071 0.04707 0.04282 -0.0628 1.0000 0.0144 -17.250 -1.3067 0.04424 0.03990 -0.0637 1.0000 0.0145 -17.000 -1.3049 0.04170 0.03728 -0.0643 1.0000 0.0146 -16.750 -1.3018 0.03941 0.03491 -0.0647 1.0000 0.0147 -16.500 -1.2971 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0.00151 -0.1108 0.8318 0.5682 -1.750 0.2546 0.00566 0.00152 -0.1107 0.7958 0.5882 -1.500 0.2822 0.00588 0.00155 -0.1105 0.7445 0.5995 -1.250 0.3094 0.00619 0.00162 -0.1102 0.6792 0.6118 -0.750 0.3598 0.00748 0.00198 -0.1093 0.4397 0.6283 -0.500 0.3868 0.00792 0.00212 -0.1092 0.3627 0.6324 -0.250 0.4142 0.00831 0.00224 -0.1091 0.2974 0.6364 0.000 0.4418 0.00866 0.00237 -0.1091 0.2419 0.6399 0.250 0.4698 0.00894 0.00250 -0.1091 0.2024 0.6428 0.500 0.4978 0.00921 0.00263 -0.1091 0.1664 0.6452 0.750 0.5258 0.00947 0.00276 -0.1091 0.1365 0.6477 1.000 0.5541 0.00969 0.00288 -0.1091 0.1177 0.6499 1.250 0.5825 0.00988 0.00301 -0.1092 0.1032 0.6518 1.500 0.6108 0.01010 0.00314 -0.1092 0.0891 0.6538 1.750 0.6390 0.01030 0.00328 -0.1092 0.0779 0.6560 2.000 0.6672 0.01049 0.00343 -0.1092 0.0698 0.6584 2.250 0.6953 0.01068 0.00359 -0.1091 0.0642 0.6606 2.500 0.7236 0.01085 0.00375 -0.1091 0.0609 0.6626 2.750 0.7518 0.01102 0.00391 -0.1091 0.0580 0.6645 3.000 0.7797 0.01123 0.00408 -0.1090 0.0547 0.6663 3.250 0.8078 0.01141 0.00425 -0.1089 0.0526 0.6681 3.500 0.8358 0.01159 0.00443 -0.1089 0.0507 0.6697 3.750 0.8635 0.01180 0.00461 -0.1087 0.0484 0.6711 4.000 0.8911 0.01201 0.00482 -0.1086 0.0460 0.6731 4.250 0.9189 0.01219 0.00502 -0.1085 0.0440 0.6750 4.500 0.9463 0.01241 0.00523 -0.1083 0.0414 0.6769 4.750 0.9736 0.01264 0.00545 -0.1081 0.0392 0.6790 5.000 1.0008 0.01286 0.00568 -0.1079 0.0368 0.6812 5.250 1.0277 0.01313 0.00592 -0.1076 0.0340 0.6833 5.500 1.0546 0.01338 0.00617 -0.1074 0.0318 0.6853 5.750 1.0811 0.01368 0.00644 -0.1070 0.0295 0.6870 6.000 1.1077 0.01395 0.00672 -0.1067 0.0281 0.6886 6.250 1.1340 0.01424 0.00702 -0.1063 0.0268 0.6906 6.500 1.1600 0.01457 0.00735 -0.1059 0.0254 0.6927 6.750 1.1860 0.01488 0.00769 -0.1055 0.0245 0.6947 7.000 1.2118 0.01519 0.00804 -0.1050 0.0238 0.6966 7.250 1.2374 0.01553 0.00839 -0.1045 0.0230 0.6986 7.500 1.2626 0.01590 0.00877 -0.1040 0.0222 0.7006 7.750 1.2874 0.01631 0.00920 -0.1034 0.0214 0.7026 8.000 1.3123 0.01669 0.00960 -0.1028 0.0208 0.7044 8.250 1.3371 0.01705 0.00999 -0.1022 0.0203 0.7061 8.750 1.3858 0.01784 0.01086 -0.1008 0.0194 0.7098 9.000 1.4095 0.01826 0.01133 -0.1000 0.0189 0.7119 9.250 1.4329 0.01872 0.01182 -0.0992 0.0185 0.7142 9.500 1.4556 0.01923 0.01236 -0.0983 0.0180 0.7166 9.750 1.4774 0.01981 0.01299 -0.0972 0.0176 0.7190 10.000 1.5000 0.02028 0.01351 -0.0962 0.0174 0.7214 10.250 1.5220 0.02076 0.01405 -0.0952 0.0171 0.7236 10.500 1.5435 0.02128 0.01462 -0.0941 0.0169 0.7257 10.750 1.5645 0.02181 0.01521 -0.0929 0.0166 0.7280 11.000 1.5848 0.02236 0.01583 -0.0916 0.0164 0.7303 11.250 1.6045 0.02294 0.01647 -0.0902 0.0161 0.7327 11.500 1.6235 0.02355 0.01714 -0.0887 0.0159 0.7351 11.750 1.6415 0.02418 0.01783 -0.0871 0.0156 0.7376 12.000 1.6581 0.02484 0.01856 -0.0853 0.0154 0.7400 12.250 1.6732 0.02555 0.01932 -0.0832 0.0152 0.7424 12.500 1.6865 0.02631 0.02014 -0.0809 0.0150 0.7445 12.750 1.6953 0.02712 0.02104 -0.0777 0.0148 0.7469 13.000 1.7036 0.02813 0.02213 -0.0748 0.0145 0.7494 13.250 1.7137 0.02906 0.02314 -0.0721 0.0144 0.7520 13.500 1.7242 0.02998 0.02415 -0.0697 0.0143 0.7548 13.750 1.7337 0.03099 0.02526 -0.0673 0.0142 0.7575 14.000 1.7422 0.03210 0.02647 -0.0648 0.0141 0.7600 14.250 1.7499 0.03331 0.02776 -0.0624 0.0140 0.7623 14.500 1.7566 0.03462 0.02917 -0.0601 0.0139 0.7646 14.750 1.7622 0.03605 0.03072 -0.0578 0.0138 0.7671 15.000 1.7666 0.03763 0.03240 -0.0556 0.0137 0.7697 15.250 1.7701 0.03935 0.03423 -0.0535 0.0136 0.7724 15.500 1.7724 0.04124 0.03623 -0.0516 0.0135 0.7751 15.750 1.7732 0.04335 0.03844 -0.0498 0.0134 0.7776 16.000 1.7727 0.04569 0.04090 -0.0482 0.0133 0.7799 16.250 1.7707 0.04831 0.04365 -0.0469 0.0132 0.7823 16.500 1.7666 0.05128 0.04674 -0.0460 0.0131 0.7849 16.750 1.7605 0.05466 0.05026 -0.0454 0.0130 0.7875 17.000 1.7525 0.05851 0.05424 -0.0453 0.0130 0.7901 17.250 1.7415 0.06304 0.05892 -0.0459 0.0129 0.7924 17.500 1.7268 0.06850 0.06454 -0.0474 0.0129 0.7945 17.750 1.7077 0.07522 0.07142 -0.0502 0.0128 0.7963 18.250 1.6394 0.09612 0.09277 -0.0617 0.0128 0.7985 18.500 1.5687 0.11482 0.11178 -0.0730 0.0129 0.7978 18.750 1.4601 0.14186 0.13918 -0.0899 0.0131 0.7953