XFOIL Version 6.94 Calculated polar for: EPPLER E853 AIRFOIL 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 0.4705 0.00806 0.00235 -0.1180 0.7410 0.6173 0.500 0.5259 0.00810 0.00244 -0.1181 0.7306 0.6327 1.000 0.5825 0.00823 0.00257 -0.1183 0.7206 0.6500 1.500 0.6372 0.00824 0.00273 -0.1182 0.7104 0.6689 2.000 0.6928 0.00836 0.00290 -0.1182 0.6988 0.6914 2.500 0.7459 0.00835 0.00306 -0.1176 0.6843 0.7173 3.000 0.7977 0.00835 0.00323 -0.1167 0.6662 0.7496 3.500 0.8477 0.00833 0.00339 -0.1153 0.6444 0.7917 4.000 0.8952 0.00830 0.00362 -0.1133 0.6246 0.8503 4.500 0.9396 0.00818 0.00374 -0.1104 0.5983 1.0000 5.000 0.9875 0.00847 0.00400 -0.1088 0.5531 1.0000 5.500 1.0233 0.00933 0.00445 -0.1050 0.4420 1.0000 6.000 1.0332 0.01198 0.00589 -0.0972 0.2185 1.0000 6.500 1.0547 0.01401 0.00723 -0.0916 0.0992 1.0000 7.000 1.0808 0.01549 0.00840 -0.0868 0.0479 1.0000 7.500 1.0998 0.01718 0.00988 -0.0805 0.0139 1.0000 8.000 1.1162 0.01923 0.01203 -0.0739 0.0066 1.0000 8.500 1.1367 0.02110 0.01407 -0.0685 0.0056 1.0000 9.000 1.1508 0.02349 0.01662 -0.0627 0.0052 1.0000 9.500 1.1589 0.02681 0.02010 -0.0569 0.0050 1.0000 10.000 1.1784 0.02995 0.02347 -0.0529 0.0049 1.0000 10.500 1.2026 0.03372 0.02754 -0.0497 0.0049 1.0000 11.000 1.2283 0.03884 0.03307 -0.0472 0.0050 1.0000 11.500 1.2376 0.04293 0.03760 -0.0434 0.0051 1.0000 12.000 1.2122 0.05352 0.04929 -0.0382 0.0063 1.0000 12.500 1.1870 0.06197 0.05816 -0.0361 0.0066 1.0000 13.000 1.0759 0.08062 0.07761 -0.0425 0.0066 1.0000 13.500 1.0354 0.09533 0.09267 -0.0484 0.0067 1.0000 14.500 0.8483 0.15985 0.15826 -0.0903 0.0097 1.0000 15.000 0.8536 0.16592 0.16435 -0.0948 0.0092 1.0000 15.500 0.8259 0.18936 0.18776 -0.1049 0.0168 1.0000 16.000 0.8193 0.20344 0.20182 -0.1126 0.0158 1.0000 16.500 0.8242 0.21280 0.21119 -0.1174 0.0146 1.0000 17.000 0.8353 0.21970 0.21811 -0.1205 0.0140 1.0000 17.500 0.8361 0.23154 0.22994 -0.1264 0.0135 1.0000 18.000 0.8425 0.24119 0.23959 -0.1310 0.0123 1.0000 18.500 0.8518 0.24921 0.24764 -0.1346 0.0116 1.0000 19.000 0.8638 0.25693 0.25537 -0.1372 0.0113 1.0000 19.500 0.8658 0.26902 0.26746 -0.1432 0.0106 1.0000 20.000 0.8740 0.27839 0.27684 -0.1471 0.0099 1.0000 20.500 0.8828 0.28706 0.28552 -0.1507 0.0094 1.0000 21.500 0.8982 0.30666 0.30514 -0.1582 0.0087 1.0000