XFOIL Version 6.94 Calculated polar for: agora10 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 -0.1166 0.03846 0.02903 -0.0154 0.9992 0.4681 -2.750 -0.0948 0.03808 0.02861 -0.0158 0.9992 0.4827 -2.500 -0.0725 0.03778 0.02833 -0.0163 0.9992 0.4986 -2.250 0.0374 0.03514 0.02585 -0.0308 0.9522 0.5384 -2.000 0.0940 0.03482 0.02568 -0.0335 0.8940 0.5754 -1.750 0.1154 0.03549 0.02668 -0.0299 0.8559 0.6150 -1.500 0.1298 0.03571 0.02771 -0.0250 0.8211 0.6921 -1.250 0.1587 0.03706 0.02924 -0.0227 0.7661 1.0008 -0.750 0.2044 0.04776 0.03898 -0.0206 0.6224 1.0008 -0.500 0.2318 0.05261 0.04354 -0.0221 0.5768 1.0008 -0.250 0.2650 0.05704 0.04779 -0.0260 0.5460 1.0008 0.000 0.2870 0.06125 0.05177 -0.0259 0.5145 1.0008 0.250 0.3218 0.06513 0.05558 -0.0317 0.4944 1.0008 0.500 0.3682 0.06941 0.05991 -0.0426 0.5155 1.0008 0.750 0.3606 0.07159 0.06168 -0.0312 0.4263 1.0008 1.000 0.3853 0.07433 0.06430 -0.0329 0.4088 1.0008 1.250 0.4138 0.07793 0.06788 -0.0381 0.4040 1.0008 1.500 0.4384 0.08130 0.07120 -0.0421 0.3985 1.0008 1.750 0.4605 0.08443 0.07424 -0.0438 0.3923 1.0008 2.000 0.4803 0.08848 0.07827 -0.0483 0.3919 1.0008