XFOIL Version 6.94 Calculated polar for: woubair3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0820 0.05409 0.03153 -0.0041 0.9988 1.0012 -2.750 -0.0577 0.05422 0.03148 -0.0040 0.9988 1.0012 -2.500 -0.0330 0.05439 0.03147 -0.0040 0.9988 1.0012 -2.250 -0.0080 0.05459 0.03151 -0.0040 0.9988 1.0012 -2.000 0.0172 0.05483 0.03157 -0.0041 0.9988 1.0012 -1.750 0.0426 0.05510 0.03168 -0.0042 0.9988 1.0012 -1.500 0.0682 0.05539 0.03184 -0.0044 0.9988 1.0012 -1.250 0.0939 0.05571 0.03204 -0.0046 0.9988 1.0012 -1.000 0.1198 0.05605 0.03229 -0.0048 0.9988 1.0012 -0.750 0.1458 0.05642 0.03262 -0.0050 0.9988 1.0012 -0.500 0.1719 0.05681 0.03303 -0.0052 0.9988 1.0012 -0.250 0.1982 0.05722 0.03354 -0.0054 0.9988 1.0012 0.000 0.2247 0.05765 0.03415 -0.0057 0.9988 1.0012 0.250 0.2515 0.05810 0.03488 -0.0060 0.9988 1.0012 0.500 0.2788 0.05858 0.03578 -0.0065 0.9988 1.0012 0.750 0.3068 0.05913 0.03691 -0.0073 0.9988 1.0012 1.000 0.3351 0.05988 0.03843 -0.0086 0.9988 1.0012 1.250 0.3599 0.06135 0.04085 -0.0108 0.9988 1.0012 1.500 0.3668 0.06505 0.04533 -0.0136 0.9988 1.0012 1.750 0.3529 0.07087 0.05123 -0.0158 0.9988 1.0012 2.000 0.3449 0.07599 0.05624 -0.0179 0.9988 1.0012 2.250 0.3437 0.08044 0.06060 -0.0201 0.9988 1.0012 2.500 0.3460 0.08451 0.06458 -0.0222 0.9988 1.0012 2.750 0.3503 0.08833 0.06833 -0.0243 0.9988 1.0012 3.000 0.3561 0.09201 0.07194 -0.0263 0.9988 1.0012 3.250 0.3630 0.09560 0.07546 -0.0282 0.9988 1.0012 3.500 0.3706 0.09912 0.07894 -0.0301 0.9988 1.0012 3.750 0.3954 0.10335 0.08316 -0.0359 0.9848 1.0012 4.000 0.4206 0.10776 0.08754 -0.0415 0.9700 1.0012 4.500 0.4467 0.11552 0.09521 -0.0468 0.9638 1.0012 4.750 0.4561 0.11898 0.09863 -0.0486 0.9623 1.0012 5.000 0.4655 0.12253 0.10213 -0.0503 0.9622 1.0012