XFOIL Version 6.94 Calculated polar for: E385 (8.41%) 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 0.7067 0.00718 0.00247 -0.1580 0.6848 1.0000 0.500 0.7639 0.00736 0.00246 -0.1583 0.6732 1.0000 1.000 0.8207 0.00757 0.00254 -0.1585 0.6620 1.0000 1.500 0.8772 0.00782 0.00264 -0.1587 0.6514 1.0000 2.000 0.9332 0.00802 0.00278 -0.1587 0.6397 1.0000 2.500 0.9888 0.00824 0.00296 -0.1587 0.6269 1.0000 3.000 1.0439 0.00847 0.00316 -0.1586 0.6135 1.0000 3.500 1.0985 0.00871 0.00337 -0.1584 0.5993 1.0000 4.000 1.1526 0.00895 0.00364 -0.1581 0.5838 1.0000 4.500 1.2063 0.00921 0.00392 -0.1577 0.5675 1.0000 5.000 1.2588 0.00945 0.00423 -0.1571 0.5450 1.0000 5.500 1.3080 0.00982 0.00453 -0.1559 0.5057 1.0000 6.000 1.3548 0.01045 0.00501 -0.1543 0.4480 1.0000 6.500 1.3954 0.01166 0.00588 -0.1519 0.3598 1.0000 7.000 1.4204 0.01428 0.00762 -0.1474 0.2103 1.0000 7.500 1.4404 0.01718 0.00971 -0.1423 0.0844 1.0000 8.000 1.4563 0.01997 0.01209 -0.1362 0.0184 1.0000 8.500 1.4772 0.02181 0.01407 -0.1306 0.0143 1.0000 9.000 1.4956 0.02386 0.01635 -0.1252 0.0132 1.0000 9.500 1.5085 0.02650 0.01921 -0.1196 0.0125 1.0000 10.000 1.5165 0.02982 0.02279 -0.1144 0.0120 1.0000 10.500 1.5229 0.03370 0.02688 -0.1101 0.0114 1.0000 11.000 1.5280 0.03816 0.03154 -0.1065 0.0108 1.0000 11.500 1.5311 0.04329 0.03690 -0.1034 0.0105 1.0000 12.000 1.5359 0.04870 0.04255 -0.1007 0.0103 1.0000 12.500 1.5440 0.05432 0.04844 -0.0982 0.0101 1.0000 13.000 1.5553 0.06027 0.05471 -0.0959 0.0100 1.0000 13.500 1.5623 0.06710 0.06194 -0.0941 0.0100 1.0000 14.000 1.5586 0.07512 0.07039 -0.0933 0.0100 1.0000 14.500 1.5438 0.08474 0.08055 -0.0938 0.0105 1.0000 15.000 1.4867 0.10358 0.10032 -0.0978 0.0121 1.0000 15.500 1.4437 0.12018 0.11739 -0.1048 0.0128 1.0000 16.000 1.4035 0.13777 0.13534 -0.1146 0.0133 1.0000 16.500 1.1338 0.14696 0.14519 -0.1144 0.0120 1.0000 17.000 1.0870 0.16902 0.16755 -0.1282 0.0122 1.0000