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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1007 0.04250 0.02776 -0.0241 0.9993 0.4808 -2.750 -0.0739 0.04204 0.02726 -0.0246 0.9993 0.4907 -2.500 -0.0468 0.04171 0.02691 -0.0251 0.9993 0.5013 -2.250 -0.0192 0.04154 0.02668 -0.0257 0.9993 0.5114 -2.000 0.0066 0.04132 0.02662 -0.0259 0.9993 0.5279 -1.750 0.0313 0.04111 0.02670 -0.0258 0.9993 0.5533 -1.500 0.0549 0.04082 0.02693 -0.0255 0.9993 0.5897 -1.250 0.0753 0.04014 0.02729 -0.0240 0.9993 0.6866 -1.000 0.0923 0.04007 0.02738 -0.0237 0.9993 1.0007 -0.750 0.1168 0.04109 0.02800 -0.0244 0.9993 1.0007 -0.500 0.1383 0.04218 0.02879 -0.0245 0.9993 1.0007 -0.250 0.1577 0.04336 0.02975 -0.0245 0.9993 1.0007 0.000 0.1750 0.04469 0.03092 -0.0243 0.9993 1.0007 0.250 0.1903 0.04624 0.03237 -0.0242 0.9993 1.0007 0.500 0.2028 0.04811 0.03421 -0.0243 0.9993 1.0007 0.750 0.2109 0.05054 0.03666 -0.0247 0.9993 1.0007 1.000 0.2122 0.05385 0.04005 -0.0256 0.9993 1.0007 1.250 0.3463 0.05699 0.04299 -0.0503 0.9170 1.0007 1.500 0.4277 0.05852 0.04441 -0.0620 0.8576 1.0007 1.750 0.4790 0.05994 0.04572 -0.0675 0.8175 1.0007 2.000 0.5261 0.06115 0.04686 -0.0717 0.7863 1.0007 2.250 0.5577 0.06280 0.04843 -0.0735 0.7615 1.0007 2.500 0.5854 0.06473 0.05029 -0.0750 0.7424 1.0007 2.750 0.6007 0.06745 0.05296 -0.0754 0.7294 1.0007 3.000 0.6144 0.07037 0.05586 -0.0757 0.7196 1.0007 3.250 0.6082 0.07427 0.05971 -0.0742 0.7136 1.0007 3.500 0.6126 0.07774 0.06315 -0.0739 0.7088 1.0007 3.750 0.6248 0.08094 0.06632 -0.0745 0.7040 1.0007 4.000 0.6194 0.08473 0.07009 -0.0733 0.7018 1.0007 4.250 0.6186 0.08833 0.07366 -0.0727 0.7001 1.0007 4.500 0.6195 0.09195 0.07727 -0.0725 0.7004 1.0007 4.750 0.6265 0.09572 0.08104 -0.0733 0.7043 1.0007 5.000 0.6144 0.09997 0.08529 -0.0725 0.7169 1.0007