XFOIL Version 6.94 Calculated polar for: Eif385mod4 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.1118 0.03945 0.02821 -0.0403 0.3319 0.4648 -2.750 0.1387 0.03828 0.02679 -0.0406 0.3229 0.4830 -2.500 0.1680 0.03735 0.02567 -0.0411 0.3146 0.5021 -2.250 0.1961 0.03600 0.02423 -0.0413 0.3077 0.5194 -2.000 0.2282 0.03533 0.02335 -0.0421 0.3029 0.5332 -1.750 0.2666 0.03524 0.02295 -0.0440 0.2992 0.5461 -1.500 0.3040 0.03469 0.02243 -0.0454 0.2970 0.5589 -1.250 0.3409 0.03440 0.02222 -0.0467 0.2952 0.5743 -1.000 0.3768 0.03438 0.02231 -0.0478 0.2937 0.5883 -0.750 0.4113 0.03453 0.02267 -0.0487 0.2926 0.5987 -0.500 0.4436 0.03476 0.02322 -0.0491 0.2919 0.6162 -0.250 0.4736 0.03496 0.02392 -0.0490 0.2916 0.6585 0.000 0.5177 0.03523 0.02471 -0.0517 0.2915 1.0007 0.250 0.5505 0.03640 0.02579 -0.0526 0.2919 1.0007 0.500 0.5822 0.03762 0.02698 -0.0533 0.2919 1.0007 0.750 0.6130 0.03890 0.02825 -0.0539 0.2917 1.0007 1.000 0.6429 0.04024 0.02960 -0.0543 0.2912 1.0007 1.250 0.6720 0.04167 0.03107 -0.0547 0.2909 1.0007 1.500 0.6924 0.04353 0.03268 -0.0536 0.2912 0.6815 1.750 0.7258 0.04614 0.03468 -0.0554 0.2928 0.5520 2.000 0.7544 0.04836 0.03679 -0.0560 0.2950 0.5367 2.250 0.7817 0.05079 0.03916 -0.0565 0.2972 0.5256 2.500 0.8084 0.05347 0.04186 -0.0569 0.2995 0.5177 2.750 0.8317 0.05432 0.04343 -0.0572 0.3082 0.5139 3.000 0.8525 0.05735 0.04678 -0.0577 0.3163 0.5109 3.250 0.8745 0.06062 0.05014 -0.0581 0.3224 0.5069 3.750 0.8860 0.07023 0.06088 -0.0606 0.3629 0.5013 4.000 0.8832 0.08037 0.07140 -0.0656 0.4093 0.5002 4.250 0.5131 0.11621 0.10943 -0.0784 0.6993 0.8182 4.500 0.5325 0.11984 0.11227 -0.0794 0.6817 0.5608 4.750 0.5505 0.12293 0.11498 -0.0796 0.6637 0.5391