XFOIL Version 6.96 Calculated polar for: EPPLER 1200 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 ------ -------- --------- --------- -------- -------- -------- -18.000 -0.7380 0.09690 0.09424 -0.0755 1.0000 0.0105 -17.750 -0.7735 0.08696 0.08415 -0.0809 1.0000 0.0104 -17.500 -0.8006 0.07872 0.07576 -0.0855 1.0000 0.0105 -17.250 -0.8222 0.07161 0.06853 -0.0894 1.0000 0.0104 -17.000 -0.8315 0.06486 0.06163 -0.0951 0.9991 0.0105 -16.750 -0.8476 0.05864 0.05528 -0.0986 0.9919 0.0105 -16.500 -0.8512 0.05367 0.05018 -0.1026 0.9819 0.0106 -16.250 -0.8340 0.04854 0.04487 -0.1110 0.9552 0.0106 -16.000 -0.8024 0.04379 0.03993 -0.1215 0.9424 0.0107 -15.750 -0.7674 0.03978 0.03571 -0.1314 0.9281 0.0108 -15.500 -0.7377 0.03717 0.03280 -0.1379 0.8914 0.0109 -15.250 -0.7377 0.03513 0.03054 -0.1378 0.8628 0.0109 -15.000 -0.7352 0.03348 0.02874 -0.1373 0.8457 0.0109 -14.750 -0.7331 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0.6464 0.6283 0.000 0.5180 0.00650 0.00174 -0.1124 0.6407 0.6375 0.250 0.5466 0.00653 0.00177 -0.1125 0.6346 0.6459 0.500 0.5748 0.00659 0.00179 -0.1127 0.6293 0.6517 0.750 0.6036 0.00661 0.00183 -0.1129 0.6235 0.6560 1.000 0.6315 0.00666 0.00185 -0.1130 0.6166 0.6590 1.250 0.6598 0.00671 0.00188 -0.1131 0.6098 0.6616 1.500 0.6872 0.00678 0.00191 -0.1131 0.6005 0.6640 1.750 0.7149 0.00686 0.00195 -0.1131 0.5909 0.6660 2.000 0.7414 0.00695 0.00201 -0.1130 0.5790 0.6683 2.250 0.7672 0.00707 0.00208 -0.1126 0.5640 0.6706 2.500 0.7919 0.00724 0.00218 -0.1121 0.5447 0.6729 2.750 0.8151 0.00747 0.00231 -0.1113 0.5218 0.6751 3.000 0.8361 0.00779 0.00249 -0.1101 0.4915 0.6774 3.250 0.8561 0.00814 0.00271 -0.1088 0.4610 0.6799 3.500 0.8765 0.00848 0.00291 -0.1075 0.4351 0.6821 4.000 0.9148 0.00917 0.00338 -0.1045 0.3834 0.6862 4.250 0.9337 0.00949 0.00361 -0.1030 0.3623 0.6884 4.500 0.9515 0.00981 0.00385 -0.1013 0.3427 0.6909 4.750 0.9672 0.01011 0.00407 -0.0991 0.3242 0.6935 5.000 0.9829 0.01041 0.00431 -0.0970 0.3087 0.6961 5.250 0.9990 0.01075 0.00458 -0.0950 0.2936 0.6983 5.750 1.0324 0.01142 0.00515 -0.0913 0.2677 0.7027 6.000 1.0494 0.01174 0.00546 -0.0895 0.2576 0.7054 6.250 1.0652 0.01213 0.00580 -0.0877 0.2464 0.7082 6.500 1.0827 0.01246 0.00612 -0.0861 0.2378 0.7109 6.750 1.0988 0.01286 0.00649 -0.0844 0.2291 0.7135 7.000 1.1150 0.01327 0.00687 -0.0827 0.2202 0.7160 7.250 1.1313 0.01369 0.00728 -0.0811 0.2129 0.7185 7.500 1.1479 0.01410 0.00770 -0.0796 0.2062 0.7215 7.750 1.1636 0.01457 0.00817 -0.0781 0.1999 0.7247 8.000 1.1804 0.01503 0.00863 -0.0767 0.1937 0.7279 8.250 1.1951 0.01559 0.00917 -0.0751 0.1867 0.7310 8.500 1.2119 0.01608 0.00967 -0.0738 0.1814 0.7339 8.750 1.2272 0.01665 0.01024 -0.0724 0.1751 0.7369 9.000 1.2422 0.01724 0.01084 -0.0710 0.1692 0.7406 9.250 1.2586 0.01779 0.01142 -0.0698 0.1647 0.7446 9.500 1.2731 0.01846 0.01208 -0.0684 0.1588 0.7486 10.000 1.3038 0.01976 0.01341 -0.0660 0.1487 0.7564 10.250 1.3176 0.02051 0.01416 -0.0646 0.1434 0.7609 10.500 1.3327 0.02120 0.01489 -0.0635 0.1389 0.7655 10.750 1.3450 0.02208 0.01574 -0.0621 0.1310 0.7701 11.000 1.3596 0.02283 0.01653 -0.0610 0.1278 0.7759 11.250 1.3735 0.02363 0.01735 -0.0599 0.1222 0.7820 11.500 1.3843 0.02465 0.01835 -0.0585 0.1147 0.7883 11.750 1.3987 0.02545 0.01921 -0.0574 0.1111 0.7957 12.000 1.4109 0.02641 0.02018 -0.0563 0.1058 0.8029 12.250 1.4223 0.02743 0.02122 -0.0551 0.1002 0.8117 12.500 1.4322 0.02857 0.02236 -0.0538 0.0927 0.8213 12.750 1.4438 0.02962 0.02345 -0.0527 0.0886 0.8333 13.000 1.4557 0.03062 0.02452 -0.0516 0.0844 0.8491 13.250 1.4639 0.03183 0.02579 -0.0501 0.0793 0.8742 13.750 1.4849 0.03413 0.02826 -0.0483 0.0703 1.0000 14.250 1.5075 0.03667 0.03084 -0.0467 0.0639 1.0000 14.500 1.5152 0.03826 0.03243 -0.0459 0.0595 1.0000 14.750 1.5258 0.03964 0.03382 -0.0452 0.0566 1.0000 15.000 1.5338 0.04128 0.03548 -0.0444 0.0527 1.0000 15.250 1.5416 0.04297 0.03717 -0.0438 0.0495 1.0000 15.500 1.5504 0.04460 0.03883 -0.0432 0.0468 1.0000 15.750 1.5563 0.04653 0.04077 -0.0426 0.0431 1.0000 16.000 1.5634 0.04839 0.04266 -0.0421 0.0407 1.0000 16.250 1.5709 0.05025 0.04455 -0.0417 0.0384 1.0000 16.500 1.5744 0.05256 0.04688 -0.0412 0.0354 1.0000 16.750 1.5804 0.05466 0.04901 -0.0409 0.0329 1.0000 17.000 1.5829 0.05718 0.05156 -0.0406 0.0301 1.0000 17.250 1.5865 0.05962 0.05404 -0.0405 0.0279 1.0000 17.500 1.5867 0.06251 0.05696 -0.0404 0.0249 1.0000 17.750 1.5895 0.06519 0.05970 -0.0405 0.0235 1.0000 18.000 1.5891 0.06830 0.06285 -0.0406 0.0211 1.0000 18.250 1.5894 0.07139 0.06599 -0.0409 0.0196 1.0000 18.500 1.5872 0.07488 0.06953 -0.0414 0.0175 1.0000 18.750 1.5832 0.07870 0.07341 -0.0420 0.0155 1.0000 19.000 1.5776 0.08284 0.07762 -0.0429 0.0135 1.0000 19.250 1.5731 0.08691 0.08176 -0.0439 0.0118 1.0000