XFOIL Version 6.94 Calculated polar for: E207 (12.04%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2544 0.00868 0.00310 -0.0471 0.6325 0.9280 0.500 0.3394 0.00894 0.00322 -0.0528 0.6170 0.9679 1.000 0.4324 0.00912 0.00325 -0.0607 0.6020 0.9894 1.500 0.5086 0.00922 0.00324 -0.0654 0.5877 1.0000 2.000 0.5537 0.00939 0.00333 -0.0635 0.5751 1.0000 2.500 0.6007 0.00962 0.00347 -0.0619 0.5631 1.0000 3.000 0.6481 0.00983 0.00367 -0.0603 0.5499 1.0000 3.500 0.6958 0.01005 0.00389 -0.0587 0.5358 1.0000 4.000 0.7438 0.01029 0.00415 -0.0571 0.5210 1.0000 4.500 0.7917 0.01052 0.00440 -0.0555 0.5052 1.0000 5.000 0.8395 0.01075 0.00469 -0.0538 0.4885 1.0000 5.500 0.8869 0.01099 0.00497 -0.0521 0.4703 1.0000 6.000 0.9339 0.01126 0.00527 -0.0503 0.4500 1.0000 6.500 0.9803 0.01153 0.00566 -0.0484 0.4252 1.0000 7.000 1.0252 0.01188 0.00607 -0.0464 0.3937 1.0000 7.500 1.0676 0.01242 0.00661 -0.0439 0.3519 1.0000 8.000 1.1027 0.01344 0.00740 -0.0406 0.2781 1.0000 8.500 1.1255 0.01534 0.00880 -0.0358 0.1849 1.0000 9.000 1.1476 0.01724 0.01038 -0.0310 0.1232 1.0000 9.500 1.1665 0.01903 0.01203 -0.0258 0.0847 1.0000 10.000 1.1791 0.02084 0.01377 -0.0197 0.0590 1.0000 10.500 1.1815 0.02348 0.01630 -0.0135 0.0335 1.0000 11.000 1.1733 0.02738 0.02030 -0.0078 0.0211 1.0000 11.500 1.1751 0.03127 0.02437 -0.0047 0.0180 1.0000 12.000 1.1608 0.03721 0.03048 -0.0024 0.0161 1.0000 12.500 1.1642 0.04195 0.03549 -0.0012 0.0149 1.0000 13.000 1.1666 0.04698 0.04073 -0.0004 0.0142 1.0000 13.500 1.1686 0.05227 0.04621 0.0001 0.0134 1.0000 14.000 1.1688 0.05802 0.05208 -0.0005 0.0121 1.0000 14.500 1.1678 0.06414 0.05840 -0.0005 0.0117 1.0000 15.000 1.1629 0.07130 0.06587 -0.0004 0.0113 1.0000 15.500 1.1557 0.07931 0.07422 -0.0027 0.0111 1.0000 16.000 1.1418 0.08889 0.08416 -0.0060 0.0111 1.0000 16.500 1.1232 0.09989 0.09552 -0.0109 0.0110 1.0000 17.000 1.0970 0.11310 0.10910 -0.0176 0.0110 1.0000 17.500 1.0678 0.12788 0.12422 -0.0258 0.0111 1.0000 18.000 1.0327 0.14538 0.14203 -0.0363 0.0112 1.0000