XFOIL Version 6.96 Calculated polar for: E211 (10.96%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5057 0.08394 0.08239 -0.0355 1.0000 0.0133 -9.500 -0.5200 0.07804 0.07652 -0.0376 1.0000 0.0134 -9.250 -0.5400 0.07115 0.06967 -0.0404 1.0000 0.0135 -9.000 -0.6037 0.04447 0.04250 -0.0690 0.9933 0.0133 -8.750 -0.5917 0.03972 0.03750 -0.0735 0.9891 0.0134 -8.500 -0.5704 0.03624 0.03380 -0.0774 0.9867 0.0138 -8.250 -0.5578 0.02535 0.02185 -0.0824 0.9844 0.0116 -8.000 -0.5413 0.02274 0.01894 -0.0817 0.9796 0.0116 -7.750 -0.5142 0.02033 0.01623 -0.0830 0.9774 0.0115 -7.500 -0.4842 0.01846 0.01410 -0.0843 0.9759 0.0115 -7.250 -0.4526 0.01699 0.01245 -0.0858 0.9747 0.0115 -7.000 -0.4201 0.01566 0.01096 -0.0873 0.9738 0.0116 -6.750 -0.3864 0.01470 0.00989 -0.0889 0.9730 0.0117 -6.500 -0.3515 0.01402 0.00913 -0.0907 0.9724 0.0120 -6.250 -0.3318 0.01326 0.00829 -0.0891 0.9668 0.0122 -6.000 -0.3004 0.01254 0.00751 -0.0901 0.9646 0.0123 -5.750 -0.2685 0.01132 0.00618 -0.0914 0.9629 0.0128 -5.500 -0.2341 0.01054 0.00534 -0.0931 0.9616 0.0135 -5.250 -0.1987 0.01002 0.00477 -0.0949 0.9606 0.0140 -5.000 -0.1624 0.00958 0.00429 -0.0969 0.9598 0.0147 -4.750 -0.1406 0.00921 0.00389 -0.0955 0.9532 0.0152 -4.500 -0.1076 0.00884 0.00348 -0.0967 0.9505 0.0159 -4.250 -0.0727 0.00849 0.00310 -0.0982 0.9485 0.0169 -4.000 -0.0370 0.00808 0.00268 -0.0999 0.9468 0.0211 -3.750 -0.0153 0.00760 0.00235 -0.0986 0.9383 0.0514 -3.500 0.0191 0.00707 0.00205 -0.1002 0.9343 0.1080 -3.250 0.0497 0.00669 0.00183 -0.1010 0.9264 0.1573 -3.000 0.0873 0.00622 0.00159 -0.1033 0.9202 0.2289 -2.750 0.1226 0.00573 0.00138 -0.1053 0.9094 0.3191 -2.500 0.1583 0.00527 0.00120 -0.1073 0.8957 0.4202 -2.250 0.1913 0.00505 0.00111 -0.1085 0.8776 0.4980 -2.000 0.2207 0.00502 0.00107 -0.1087 0.8561 0.5318 -1.750 0.2484 0.00506 0.00105 -0.1086 0.8338 0.5580 -1.500 0.2751 0.00513 0.00104 -0.1082 0.8119 0.5738 -1.250 0.3013 0.00520 0.00104 -0.1078 0.7905 0.5853 -1.000 0.3276 0.00528 0.00104 -0.1074 0.7705 0.5956 -0.750 0.3538 0.00536 0.00106 -0.1069 0.7512 0.6064 -0.500 0.3801 0.00545 0.00108 -0.1065 0.7331 0.6163 -0.250 0.4064 0.00553 0.00110 -0.1061 0.7161 0.6251 0.000 0.4329 0.00562 0.00113 -0.1058 0.6999 0.6343 0.250 0.4594 0.00568 0.00116 -0.1055 0.6842 0.6432 0.500 0.4860 0.00577 0.00120 -0.1052 0.6687 0.6521 0.750 0.5125 0.00585 0.00125 -0.1049 0.6528 0.6613 1.000 0.5391 0.00593 0.00130 -0.1046 0.6370 0.6704 1.500 0.5923 0.00610 0.00142 -0.1040 0.6078 0.6900 1.750 0.6189 0.00618 0.00148 -0.1037 0.5936 0.7000 2.000 0.6455 0.00628 0.00156 -0.1035 0.5788 0.7102 2.250 0.6720 0.00636 0.00163 -0.1032 0.5640 0.7202 2.500 0.6985 0.00646 0.00171 -0.1029 0.5490 0.7304 2.750 0.7249 0.00656 0.00180 -0.1026 0.5333 0.7414 3.000 0.7512 0.00666 0.00191 -0.1023 0.5173 0.7535 3.250 0.7774 0.00677 0.00201 -0.1019 0.5010 0.7665 3.500 0.8034 0.00688 0.00213 -0.1016 0.4845 0.7806 3.750 0.8289 0.00702 0.00225 -0.1011 0.4656 0.7960 4.250 0.8770 0.00746 0.00258 -0.0997 0.4042 0.8335 4.500 0.8996 0.00777 0.00278 -0.0987 0.3635 0.8571 4.750 0.9209 0.00806 0.00301 -0.0974 0.3247 0.8864 5.000 0.9374 0.00833 0.00323 -0.0950 0.2857 0.9390 5.250 0.9613 0.00889 0.00354 -0.0945 0.2298 1.0000 5.500 0.9829 0.00949 0.00389 -0.0935 0.1811 1.0000 5.750 1.0048 0.01005 0.00425 -0.0926 0.1421 1.0000 6.000 1.0273 0.01054 0.00459 -0.0918 0.1125 1.0000 6.250 1.0489 0.01111 0.00498 -0.0909 0.0826 1.0000 6.500 1.0708 0.01163 0.00537 -0.0899 0.0592 1.0000 6.750 1.0905 0.01234 0.00589 -0.0886 0.0309 1.0000 7.000 1.1095 0.01309 0.00651 -0.0871 0.0127 1.0000 7.250 1.1317 0.01356 0.00699 -0.0861 0.0105 1.0000 7.500 1.1539 0.01399 0.00747 -0.0852 0.0097 1.0000 7.750 1.1751 0.01451 0.00802 -0.0841 0.0088 1.0000 8.000 1.1938 0.01522 0.00880 -0.0825 0.0080 1.0000 8.250 1.2140 0.01576 0.00941 -0.0812 0.0078 1.0000 8.500 1.2336 0.01633 0.01003 -0.0799 0.0076 1.0000 8.750 1.2525 0.01692 0.01067 -0.0784 0.0074 1.0000 9.000 1.2700 0.01756 0.01138 -0.0767 0.0073 1.0000 9.250 1.2853 0.01822 0.01210 -0.0746 0.0071 1.0000 9.500 1.2989 0.01893 0.01288 -0.0722 0.0069 1.0000 9.750 1.3122 0.01965 0.01368 -0.0698 0.0068 1.0000 10.000 1.3235 0.02049 0.01459 -0.0672 0.0067 1.0000 10.250 1.3355 0.02129 0.01545 -0.0648 0.0065 1.0000 10.500 1.3458 0.02221 0.01644 -0.0623 0.0063 1.0000 10.750 1.3545 0.02324 0.01754 -0.0596 0.0062 1.0000 11.000 1.3621 0.02437 0.01875 -0.0569 0.0061 1.0000 11.250 1.3658 0.02582 0.02028 -0.0539 0.0059 1.0000 11.500 1.3686 0.02742 0.02198 -0.0509 0.0058 1.0000 11.750 1.3662 0.02963 0.02433 -0.0477 0.0057 1.0000 12.000 1.3629 0.03227 0.02711 -0.0447 0.0056 1.0000 12.250 1.3626 0.03485 0.02984 -0.0424 0.0056 1.0000 12.500 1.3670 0.03664 0.03175 -0.0407 0.0055 1.0000 12.750 1.3708 0.03845 0.03369 -0.0391 0.0055 1.0000 13.000 1.3723 0.04068 0.03605 -0.0377 0.0055 1.0000 13.250 1.3722 0.04322 0.03873 -0.0365 0.0054 1.0000 13.500 1.3709 0.04594 0.04158 -0.0355 0.0054 1.0000 13.750 1.3689 0.04884 0.04463 -0.0349 0.0054 1.0000 14.000 1.3666 0.05186 0.04779 -0.0347 0.0053 1.0000 14.250 1.3614 0.05545 0.05153 -0.0347 0.0053 1.0000 14.500 1.3552 0.05934 0.05557 -0.0352 0.0052 1.0000 14.750 1.3460 0.06389 0.06028 -0.0360 0.0052 1.0000 15.000 1.3384 0.06838 0.06492 -0.0374 0.0052 1.0000 15.250 1.3261 0.07390 0.07061 -0.0392 0.0052 1.0000 15.500 1.3121 0.08000 0.07688 -0.0417 0.0052 1.0000 15.750 1.2975 0.08652 0.08355 -0.0447 0.0052 1.0000 16.000 1.2813 0.09371 0.09091 -0.0483 0.0053 1.0000 16.250 1.2647 0.10139 0.09875 -0.0525 0.0053 1.0000 16.500 1.2461 0.10983 0.10736 -0.0573 0.0053 1.0000 16.750 1.2274 0.11875 0.11643 -0.0627 0.0053 1.0000 17.000 1.2077 0.12835 0.12619 -0.0687 0.0054 1.0000 17.250 1.1849 0.13912 0.13710 -0.0755 0.0054 1.0000