XFOIL Version 6.94 Calculated polar for: Eif385mod3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0973 0.04205 0.03204 -0.0104 0.9993 0.5222 -2.750 -0.0606 0.04147 0.03141 -0.0127 0.9993 0.5128 -2.500 -0.0241 0.04103 0.03101 -0.0146 0.9993 0.5087 -1.750 0.2682 0.03557 0.02252 -0.0447 0.4580 0.5142 -1.500 0.3002 0.03594 0.02271 -0.0451 0.4419 0.5227 -1.250 0.3323 0.03631 0.02301 -0.0455 0.4299 0.5337 -1.000 0.3640 0.03660 0.02343 -0.0458 0.4191 0.5527 -0.750 0.3933 0.03666 0.02392 -0.0453 0.4102 0.6354 -0.500 0.4408 0.03693 0.02450 -0.0485 0.4011 1.0007 -0.250 0.4757 0.03804 0.02536 -0.0496 0.3951 1.0007 0.000 0.5103 0.03922 0.02636 -0.0507 0.3916 1.0007 0.250 0.5443 0.04050 0.02751 -0.0518 0.3892 1.0007 0.500 0.5775 0.04188 0.02882 -0.0527 0.3874 1.0007 0.750 0.6100 0.04337 0.03029 -0.0537 0.3864 1.0007 1.000 0.6415 0.04497 0.03193 -0.0547 0.3860 1.0007 1.250 0.6716 0.04668 0.03372 -0.0556 0.3863 1.0007 1.500 0.7000 0.04851 0.03571 -0.0564 0.3873 1.0007 1.750 0.7264 0.05057 0.03799 -0.0573 0.3892 1.0007 2.000 0.7501 0.05299 0.04067 -0.0582 0.3919 1.0007 2.250 0.7713 0.05574 0.04364 -0.0590 0.3945 1.0007 2.500 0.7897 0.05879 0.04691 -0.0596 0.3971 1.0007 2.750 0.8045 0.06218 0.05048 -0.0602 0.3998 1.0007 3.000 0.8155 0.06595 0.05440 -0.0605 0.4030 1.0007 3.250 0.8255 0.06990 0.05844 -0.0608 0.4064 1.0007 3.500 0.8401 0.07374 0.06229 -0.0613 0.4097 1.0007 3.750 0.7736 0.08404 0.07313 -0.0614 0.4303 1.0007 4.250 0.6337 0.10652 0.09588 -0.0667 0.5086 1.0007