XFOIL Version 6.94 Calculated polar for: E201 (11.88%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3540 0.00759 0.00224 -0.0774 0.6529 0.7608 0.500 0.4034 0.00744 0.00235 -0.0756 0.6418 0.8583 1.000 0.4683 0.00744 0.00243 -0.0769 0.6307 0.9566 1.500 0.5574 0.00753 0.00248 -0.0841 0.6189 0.9966 2.000 0.6121 0.00771 0.00257 -0.0841 0.6079 1.0000 2.500 0.6617 0.00791 0.00269 -0.0828 0.5961 1.0000 3.000 0.7118 0.00805 0.00284 -0.0817 0.5826 1.0000 3.500 0.7629 0.00823 0.00302 -0.0807 0.5684 1.0000 4.000 0.8143 0.00841 0.00320 -0.0798 0.5529 1.0000 4.500 0.8658 0.00861 0.00343 -0.0790 0.5364 1.0000 5.000 0.9169 0.00882 0.00366 -0.0780 0.5171 1.0000 5.500 0.9672 0.00910 0.00393 -0.0769 0.4952 1.0000 6.000 1.0144 0.00942 0.00423 -0.0753 0.4510 1.0000 6.500 1.0577 0.01007 0.00469 -0.0731 0.3881 1.0000 7.000 1.0895 0.01154 0.00563 -0.0693 0.2764 1.0000 7.500 1.1180 0.01330 0.00688 -0.0651 0.1796 1.0000 8.000 1.1431 0.01511 0.00825 -0.0606 0.1007 1.0000 8.500 1.1551 0.01730 0.00999 -0.0539 0.0325 1.0000 9.000 1.1677 0.01924 0.01186 -0.0473 0.0159 1.0000 9.500 1.1882 0.02092 0.01371 -0.0424 0.0139 1.0000 10.000 1.2042 0.02302 0.01596 -0.0378 0.0126 1.0000 10.500 1.2112 0.02597 0.01908 -0.0330 0.0117 1.0000 11.000 1.2102 0.02999 0.02333 -0.0288 0.0112 1.0000 11.500 1.2162 0.03391 0.02744 -0.0258 0.0109 1.0000 12.000 1.2234 0.03805 0.03178 -0.0235 0.0108 1.0000 12.500 1.2331 0.04220 0.03614 -0.0217 0.0104 1.0000 13.000 1.2423 0.04663 0.04079 -0.0201 0.0101 1.0000 13.500 1.2504 0.05139 0.04577 -0.0191 0.0096 1.0000 14.000 1.2556 0.05690 0.05161 -0.0181 0.0096 1.0000 14.500 1.2563 0.06321 0.05822 -0.0180 0.0095 1.0000 15.000 1.2494 0.07090 0.06627 -0.0188 0.0095 1.0000 15.500 1.2343 0.08024 0.07599 -0.0211 0.0094 1.0000 16.000 1.2088 0.09201 0.08819 -0.0253 0.0097 1.0000 16.500 1.1775 0.10581 0.10239 -0.0317 0.0098 1.0000 17.000 1.1421 0.12176 0.11871 -0.0406 0.0100 1.0000 17.500 1.1030 0.14041 0.13771 -0.0520 0.0102 1.0000 18.000 1.0554 0.16388 0.16148 -0.0668 0.0105 1.0000 18.500 1.0123 0.18934 0.18708 -0.0814 0.0113 1.0000