XFOIL Version 6.94 Calculated polar for: wouaibair3 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 0.2154 0.04302 0.03111 -0.0527 0.8542 0.4157 -2.750 0.2838 0.04191 0.02863 -0.0578 0.5039 0.4425 -2.500 0.3196 0.04262 0.02919 -0.0590 0.4805 0.4697 -2.250 0.3618 0.04325 0.02977 -0.0615 0.4648 0.4999 -2.000 0.4036 0.04383 0.03051 -0.0637 0.4528 0.5394 -1.750 0.4454 0.04446 0.03130 -0.0659 0.4411 0.5800 -1.500 0.4854 0.04517 0.03219 -0.0675 0.4289 0.6258 -1.250 0.5229 0.04565 0.03299 -0.0683 0.4222 0.6775 -1.000 0.5530 0.04568 0.03356 -0.0672 0.4191 0.7449 -0.750 0.5823 0.04544 0.03384 -0.0661 0.4170 0.8086 -0.500 0.6221 0.04513 0.03406 -0.0682 0.4155 0.9041 -0.250 0.6993 0.04717 0.03567 -0.0817 0.4083 1.0024 0.000 0.7544 0.04978 0.03781 -0.0887 0.4028 1.0024 0.250 0.7979 0.05207 0.04002 -0.0926 0.4038 1.0024 0.500 0.8341 0.05433 0.04235 -0.0949 0.4033 1.0024 0.750 0.8650 0.05658 0.04484 -0.0962 0.4010 1.0024 1.000 0.8968 0.05952 0.04789 -0.0978 0.4030 1.0024 1.250 0.9245 0.06202 0.05070 -0.0989 0.4064 1.0024 1.500 0.9477 0.06483 0.05385 -0.0997 0.4098 1.0024 1.750 0.9705 0.06827 0.05762 -0.1009 0.4199 1.0024 2.000 0.9879 0.07171 0.06151 -0.1024 0.4386 1.0024 2.250 0.9974 0.07574 0.06595 -0.1037 0.4590 1.0024 2.500 0.9916 0.08064 0.07122 -0.1044 0.4832 1.0024 2.750 0.9773 0.08688 0.07770 -0.1055 0.5129 1.0024 3.000 0.8938 0.09610 0.08713 -0.1030 0.5586 1.0024 3.250 0.7639 0.10938 0.10048 -0.1027 0.6338 1.0024 3.500 0.6779 0.11893 0.11005 -0.1025 0.7312 1.0024 3.750 0.5176 0.12541 0.11669 -0.0857 0.9566 1.0024 4.000 0.5060 0.12829 0.11947 -0.0825 0.9823 1.0024 4.250 0.4984 0.13072 0.12179 -0.0798 0.9964 1.0024 4.500 0.5090 0.13461 0.12556 -0.0813 0.9976 1.0024 4.750 0.5204 0.13835 0.12921 -0.0831 0.9976 1.0024 5.000 0.5318 0.14211 0.13287 -0.0849 0.9976 1.0024