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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0488 0.04362 0.02941 -0.0183 0.9988 0.6063 -2.750 -0.0243 0.04377 0.02974 -0.0174 0.9988 0.6246 -2.500 -0.0015 0.04379 0.03010 -0.0160 0.9988 0.6551 -2.250 0.0188 0.04363 0.03043 -0.0138 0.9988 0.7070 -2.000 0.0387 0.04336 0.03065 -0.0115 0.9988 0.7723 -1.750 0.0513 0.04200 0.02976 -0.0081 0.9988 1.0012 -1.500 0.0798 0.04239 0.03011 -0.0087 0.9988 1.0012 -1.250 0.1086 0.04278 0.03047 -0.0094 0.9988 1.0012 -1.000 0.1375 0.04318 0.03086 -0.0101 0.9988 1.0012 -0.750 0.1668 0.04356 0.03129 -0.0107 0.9988 1.0012 -0.500 0.1972 0.04390 0.03177 -0.0114 0.9988 1.0012 -0.250 0.2307 0.04408 0.03229 -0.0124 0.9988 1.0012 0.000 0.2714 0.04404 0.03290 -0.0150 0.9988 1.0012 0.250 0.4986 0.03886 0.02495 -0.0494 0.5231 1.0012 0.500 0.5430 0.04084 0.02631 -0.0525 0.4894 1.0012 0.750 0.5894 0.04263 0.02789 -0.0562 0.4702 1.0012 1.000 0.6330 0.04458 0.02974 -0.0594 0.4527 1.0012 1.250 0.6728 0.04670 0.03184 -0.0618 0.4348 1.0012 1.500 0.7138 0.04923 0.03436 -0.0645 0.4224 1.0012 1.750 0.7467 0.05131 0.03680 -0.0659 0.4100 1.0012 2.000 0.7827 0.05423 0.03979 -0.0678 0.4002 1.0012 2.250 0.8130 0.05679 0.04280 -0.0691 0.3948 1.0012 2.500 0.8408 0.05968 0.04599 -0.0700 0.3875 1.0012 2.750 0.8678 0.06293 0.04956 -0.0709 0.3839 1.0012 3.000 0.8904 0.06636 0.05345 -0.0719 0.3877 1.0012 3.250 0.9103 0.07016 0.05762 -0.0728 0.3916 1.0012 3.500 0.9269 0.07424 0.06199 -0.0735 0.3947 1.0012 3.750 0.9416 0.07863 0.06661 -0.0739 0.3981 1.0012 4.000 0.9388 0.08326 0.07166 -0.0742 0.4092 1.0012 4.250 0.9506 0.08877 0.07731 -0.0756 0.4216 1.0012 4.500 0.9354 0.09491 0.08375 -0.0768 0.4442 1.0012 4.750 0.8544 0.10253 0.09149 -0.0748 0.4752 1.0012 5.000 0.7930 0.11194 0.10086 -0.0777 0.5225 1.0012