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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0373 0.04297 0.02862 -0.0218 0.9988 0.4859 -2.750 -0.0120 0.04317 0.02902 -0.0213 0.9988 0.5058 -2.500 0.0132 0.04337 0.02944 -0.0207 0.9988 0.5246 -2.250 0.0379 0.04352 0.02991 -0.0200 0.9988 0.5514 -2.000 0.0620 0.04361 0.03041 -0.0191 0.9988 0.5847 -1.750 0.0859 0.04367 0.03090 -0.0182 0.9988 0.6160 -1.500 0.1082 0.04356 0.03140 -0.0167 0.9988 0.6649 -1.250 0.1258 0.04304 0.03172 -0.0136 0.9988 0.7592 -1.000 0.1384 0.04172 0.03088 -0.0103 0.9988 1.0012 -0.750 0.1696 0.04209 0.03134 -0.0113 0.9988 1.0012 -0.500 0.2028 0.04235 0.03183 -0.0124 0.9988 1.0012 0.250 0.5000 0.03856 0.02480 -0.0495 0.4497 1.0012 0.500 0.5480 0.04003 0.02598 -0.0534 0.4318 1.0012 0.750 0.5945 0.04172 0.02749 -0.0571 0.4157 1.0012 1.000 0.6370 0.04364 0.02927 -0.0600 0.3982 1.0012 1.250 0.6775 0.04550 0.03129 -0.0626 0.3863 1.0012 1.500 0.7159 0.04771 0.03366 -0.0648 0.3729 1.0012 1.750 0.7522 0.05005 0.03619 -0.0666 0.3636 1.0012 2.000 0.7856 0.05280 0.03909 -0.0680 0.3554 1.0012 2.250 0.8142 0.05529 0.04196 -0.0687 0.3481 1.0012 2.500 0.8426 0.05827 0.04532 -0.0695 0.3471 1.0012 2.750 0.8686 0.06150 0.04891 -0.0703 0.3483 1.0012 3.000 0.8919 0.06488 0.05262 -0.0708 0.3481 1.0012 3.250 0.9117 0.06849 0.05654 -0.0710 0.3488 1.0012 3.500 0.9301 0.07255 0.06088 -0.0713 0.3536 1.0012 3.750 0.9413 0.07682 0.06568 -0.0723 0.3684 1.0012 4.000 0.9471 0.08180 0.07108 -0.0736 0.3878 1.0012 4.250 0.9388 0.08777 0.07742 -0.0752 0.4150 1.0012 4.500 0.8982 0.09505 0.08498 -0.0764 0.4529 1.0012 4.750 0.8477 0.10447 0.09449 -0.0797 0.5090 1.0012 5.000 0.7134 0.11793 0.10780 -0.0861 0.6395 1.0012