XFOIL Version 6.94 Calculated polar for: E203 (13.64%) 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 0.3484 0.01006 0.00346 -0.0821 0.6831 0.6281 0.500 0.4034 0.01010 0.00354 -0.0820 0.6710 0.6513 1.000 0.4587 0.01015 0.00364 -0.0818 0.6595 0.6780 1.500 0.5129 0.01016 0.00378 -0.0814 0.6478 0.7118 2.000 0.5656 0.01017 0.00400 -0.0807 0.6361 0.7565 2.500 0.6163 0.01018 0.00424 -0.0793 0.6252 0.8193 3.000 0.6643 0.01011 0.00441 -0.0770 0.6131 0.9101 3.500 0.7492 0.01016 0.00455 -0.0831 0.5976 1.0000 4.000 0.7986 0.01037 0.00475 -0.0820 0.5831 1.0000 4.500 0.8492 0.01057 0.00496 -0.0810 0.5669 1.0000 5.000 0.8997 0.01077 0.00519 -0.0800 0.5496 1.0000 5.500 0.9496 0.01097 0.00543 -0.0788 0.5302 1.0000 6.000 0.9981 0.01120 0.00571 -0.0773 0.5072 1.0000 6.500 1.0444 0.01147 0.00602 -0.0754 0.4780 1.0000 7.000 1.0878 0.01186 0.00645 -0.0731 0.4391 1.0000 7.500 1.1222 0.01265 0.00704 -0.0692 0.3689 1.0000 8.000 1.1405 0.01433 0.00818 -0.0632 0.2658 1.0000 8.500 1.1481 0.01644 0.00978 -0.0557 0.1749 1.0000 9.000 1.1598 0.01833 0.01139 -0.0492 0.1210 1.0000 9.500 1.1726 0.02035 0.01325 -0.0435 0.0829 1.0000 10.000 1.1809 0.02284 0.01560 -0.0381 0.0505 1.0000 10.500 1.1718 0.02692 0.01955 -0.0318 0.0260 1.0000 11.000 1.1802 0.03024 0.02304 -0.0283 0.0207 1.0000 12.000 1.1876 0.03871 0.03187 -0.0231 0.0165 1.0000 12.500 1.1924 0.04328 0.03660 -0.0215 0.0154 1.0000 13.000 1.1934 0.04848 0.04194 -0.0201 0.0146 1.0000 13.500 1.1961 0.05391 0.04755 -0.0184 0.0139 1.0000 14.000 1.2071 0.05873 0.05263 -0.0175 0.0136 1.0000 14.500 1.2146 0.06429 0.05852 -0.0171 0.0133 1.0000 15.000 1.2158 0.07101 0.06560 -0.0173 0.0131 1.0000 15.500 1.2087 0.07917 0.07415 -0.0186 0.0130 1.0000 16.000 1.1922 0.08909 0.08448 -0.0217 0.0129 1.0000 16.500 1.1686 0.10085 0.09665 -0.0265 0.0129 1.0000 17.000 1.1395 0.11448 0.11067 -0.0334 0.0130 1.0000 17.500 1.1048 0.13054 0.12709 -0.0427 0.0132 1.0000 18.000 1.0626 0.15002 0.14692 -0.0549 0.0136 1.0000 20.000 0.7508 0.22660 0.22446 -0.0978 0.0271 1.0000 20.500 0.7594 0.23719 0.23505 -0.1009 0.0260 1.0000 21.000 0.7589 0.24648 0.24434 -0.1069 0.0251 1.0000 21.500 0.7649 0.25550 0.25337 -0.1114 0.0229 1.0000 22.000 0.7738 0.26357 0.26146 -0.1150 0.0216 1.0000 22.500 0.7856 0.27043 0.26834 -0.1176 0.0199 1.0000 23.500 0.8051 0.28882 0.28677 -0.1237 0.0189 1.0000 24.000 0.8063 0.29841 0.29638 -0.1292 0.0179 1.0000 24.500 0.8140 0.30734 0.30533 -0.1329 0.0166 1.0000 25.000 0.8220 0.31587 0.31388 -0.1363 0.0155 1.0000 25.500 0.8304 0.32397 0.32200 -0.1395 0.0147 1.0000 26.000 0.8402 0.33168 0.32974 -0.1421 0.0142 1.0000 26.500 0.8479 0.34203 0.34010 -0.1451 0.0138 1.0000 27.000 0.8507 0.35177 0.34986 -0.1498 0.0135 1.0000 27.500 0.8569 0.36160 0.35973 -0.1534 0.0122 1.0000 28.000 0.8633 0.37061 0.36876 -0.1568 0.0114 1.0000 28.500 0.8695 0.37953 0.37771 -0.1601 0.0109 1.0000 29.000 0.8756 0.38797 0.38617 -0.1632 0.0104 1.0000 29.500 0.8848 0.39717 0.39541 -0.1649 0.0099 1.0000 30.000 0.8880 0.40701 0.40526 -0.1687 0.0098 1.0000 30.500 0.8909 0.41670 0.41497 -0.1725 0.0098 1.0000 31.000 0.8946 0.42681 0.42511 -0.1762 0.0093 1.0000 31.500 0.8989 0.43654 0.43486 -0.1794 0.0087 1.0000 32.000 0.9029 0.44603 0.44438 -0.1826 0.0080 1.0000