XFOIL Version 6.94 Calculated polar for: E216 (10.4%) 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.8317 0.00945 0.00450 -0.1949 0.8568 0.7066 1.000 0.8973 0.00923 0.00435 -0.1963 0.8354 0.7608 1.500 0.9574 0.00913 0.00429 -0.1965 0.8100 0.8135 2.000 1.0062 0.00914 0.00432 -0.1942 0.7800 0.8681 2.500 1.0407 0.00901 0.00420 -0.1888 0.7474 0.9747 3.000 1.0992 0.00936 0.00437 -0.1893 0.7103 1.0000 3.500 1.1520 0.00983 0.00465 -0.1886 0.6714 1.0000 4.000 1.2005 0.01036 0.00505 -0.1869 0.6297 1.0000 4.500 1.2460 0.01100 0.00551 -0.1847 0.5847 1.0000 5.000 1.2893 0.01170 0.00608 -0.1821 0.5386 1.0000 5.500 1.3300 0.01252 0.00672 -0.1790 0.4911 1.0000 6.000 1.3675 0.01345 0.00749 -0.1754 0.4415 1.0000 6.500 1.4000 0.01452 0.00836 -0.1709 0.3851 1.0000 7.000 1.4309 0.01578 0.00940 -0.1663 0.3258 1.0000 7.500 1.4601 0.01725 0.01062 -0.1617 0.2676 1.0000 8.000 1.4887 0.01889 0.01205 -0.1572 0.2133 1.0000 8.500 1.5147 0.02078 0.01370 -0.1525 0.1585 1.0000 9.000 1.5392 0.02285 0.01559 -0.1478 0.1156 1.0000 9.500 1.5608 0.02519 0.01780 -0.1429 0.0771 1.0000 10.000 1.5673 0.02889 0.02122 -0.1363 0.0336 1.0000 10.500 1.5759 0.03255 0.02497 -0.1303 0.0241 1.0000 11.000 1.5855 0.03624 0.02890 -0.1252 0.0209 1.0000 11.500 1.5924 0.04039 0.03328 -0.1206 0.0191 1.0000 12.000 1.5889 0.04591 0.03903 -0.1160 0.0180 1.0000 12.500 1.5840 0.05217 0.04557 -0.1124 0.0173 1.0000 13.000 1.5859 0.05816 0.05184 -0.1099 0.0167 1.0000 13.500 1.5876 0.06462 0.05859 -0.1080 0.0162 1.0000 14.000 1.5890 0.07151 0.06579 -0.1067 0.0158 1.0000 14.500 1.5889 0.07887 0.07348 -0.1063 0.0152 1.0000 15.000 1.5858 0.08683 0.08175 -0.1068 0.0146 1.0000 15.500 1.5802 0.09553 0.09075 -0.1081 0.0142 1.0000 16.000 1.5711 0.10510 0.10065 -0.1104 0.0139 1.0000 16.500 1.5560 0.11613 0.11207 -0.1142 0.0138 1.0000 17.000 1.5361 0.12854 0.12488 -0.1200 0.0137 1.0000 17.500 1.5100 0.14313 0.13992 -0.1285 0.0138 1.0000 18.000 1.4769 0.16061 0.15787 -0.1402 0.0140 1.0000 18.500 1.4160 0.18859 0.18646 -0.1608 0.0147 1.0000