XFOIL Version 6.94 Calculated polar for: eif385mod5 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 0.1211 0.04215 0.03269 -0.0383 0.3599 0.6367 -2.750 0.1535 0.04110 0.03145 -0.0406 0.3469 0.6480 -2.500 0.1883 0.04035 0.03046 -0.0432 0.3360 0.6552 -2.250 0.2294 0.03997 0.02977 -0.0475 0.3281 0.6591 -2.000 0.2736 0.03950 0.02914 -0.0521 0.3233 0.6645 -1.750 0.3190 0.03920 0.02867 -0.0568 0.3192 0.6668 -1.500 0.3644 0.03893 0.02823 -0.0613 0.3157 0.6621 -1.250 0.4124 0.03899 0.02808 -0.0662 0.3129 0.6555 -1.000 0.4628 0.03964 0.02844 -0.0717 0.3107 0.6430 -0.750 0.5091 0.04029 0.02884 -0.0761 0.3092 0.6228 -0.500 0.5529 0.04118 0.02950 -0.0798 0.3083 0.6025 -0.250 0.5942 0.04222 0.03034 -0.0828 0.3079 0.5836 0.000 0.6330 0.04338 0.03133 -0.0852 0.3073 0.5696 0.250 0.6687 0.04446 0.03231 -0.0870 0.3064 0.5562 0.500 0.7040 0.04600 0.03369 -0.0887 0.3051 0.5415 0.750 0.7367 0.04737 0.03502 -0.0899 0.3040 0.5302 1.000 0.7691 0.04895 0.03656 -0.0910 0.3035 0.5214 1.250 0.8006 0.05012 0.03783 -0.0919 0.3047 0.5165 1.500 0.8307 0.05128 0.03925 -0.0927 0.3074 0.5109 1.750 0.8594 0.05295 0.04122 -0.0935 0.3112 0.5034 2.000 0.8871 0.05513 0.04362 -0.0943 0.3154 0.4959 2.250 0.9130 0.05740 0.04609 -0.0949 0.3198 0.4905 2.500 0.9381 0.05993 0.04875 -0.0955 0.3240 0.4851 2.750 0.9632 0.06293 0.05179 -0.0961 0.3278 0.4796 3.000 0.9776 0.06573 0.05537 -0.0971 0.3410 0.4760 3.250 0.9926 0.07003 0.05992 -0.0980 0.3517 0.4723 3.500 1.0174 0.07357 0.06347 -0.0989 0.3595 0.4684 3.750 1.0156 0.08078 0.07124 -0.1016 0.3863 0.4673 4.000 0.5767 0.12505 0.11704 -0.1180 0.7418 0.5111 4.250 0.6141 0.13002 0.12190 -0.1217 0.7339 0.5060 4.500 0.6283 0.13252 0.12431 -0.1216 0.7172 0.5018 4.750 0.6453 0.13539 0.12707 -0.1218 0.7000 0.4964 5.000 0.6642 0.13835 0.12995 -0.1221 0.6822 0.4913