XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0920 0.03879 0.02656 -0.0266 0.9993 0.3391 -2.750 -0.0673 0.03860 0.02620 -0.0266 0.9993 0.3409 -2.500 -0.0426 0.03850 0.02596 -0.0265 0.9993 0.3418 -2.250 -0.0174 0.03855 0.02583 -0.0266 0.9993 0.3427 -2.000 0.0078 0.03855 0.02577 -0.0267 0.9993 0.3449 -1.750 0.0324 0.03863 0.02586 -0.0267 0.9993 0.3489 -1.500 0.0561 0.03885 0.02612 -0.0267 0.9993 0.3566 -1.250 0.0791 0.03926 0.02651 -0.0267 0.9993 0.3647 -1.000 0.1018 0.03964 0.02703 -0.0267 0.9993 0.3721 -0.750 0.1236 0.04020 0.02772 -0.0268 0.9993 0.3798 -0.500 0.1443 0.04094 0.02860 -0.0269 0.9993 0.3915 -0.250 0.1676 0.04162 0.02958 -0.0278 0.9979 0.4080 0.000 0.2511 0.04053 0.02941 -0.0394 0.9725 0.4780 0.250 0.3377 0.03818 0.02816 -0.0498 0.9352 1.0007 0.500 0.4304 0.03626 0.02610 -0.0605 0.8915 1.0007 0.750 0.5309 0.03272 0.02249 -0.0702 0.8378 1.0007 1.000 0.5982 0.02977 0.01937 -0.0727 0.7643 1.0007 1.250 0.6409 0.02867 0.01776 -0.0719 0.6932 1.0007 1.500 0.6711 0.02896 0.01756 -0.0708 0.6432 1.0007 1.750 0.7001 0.02963 0.01786 -0.0704 0.6104 1.0007 2.000 0.7292 0.03048 0.01845 -0.0704 0.5866 1.0007 2.250 0.7583 0.03139 0.01919 -0.0707 0.5677 1.0007 2.500 0.7871 0.03236 0.02004 -0.0711 0.5523 1.0007 2.750 0.8158 0.03338 0.02096 -0.0715 0.5396 1.0007 3.000 0.8449 0.03441 0.02188 -0.0720 0.5294 1.0007 3.250 0.8715 0.03579 0.02336 -0.0727 0.5208 1.0007 3.500 0.8998 0.03703 0.02461 -0.0733 0.5139 1.0007 3.750 0.9261 0.03857 0.02623 -0.0740 0.5081 1.0007 4.000 0.9503 0.04034 0.02817 -0.0747 0.5027 1.0007 4.250 0.9758 0.04197 0.02988 -0.0752 0.4979 1.0007 4.500 1.0020 0.04357 0.03152 -0.0757 0.4933 1.0007 4.750 1.0181 0.04612 0.03439 -0.0759 0.4882 1.0007 5.000 1.0353 0.04862 0.03710 -0.0759 0.4838 1.0007