XFOIL Version 6.94 Calculated polar for: S 4110-084-84,61 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4108 0.00572 0.00188 -0.0918 0.8142 1.0000 0.500 0.4644 0.00582 0.00181 -0.0909 0.7893 1.0000 1.000 0.5181 0.00596 0.00178 -0.0900 0.7623 1.0000 1.500 0.5715 0.00613 0.00179 -0.0891 0.7318 1.0000 2.000 0.6244 0.00633 0.00185 -0.0881 0.6945 1.0000 2.500 0.6766 0.00663 0.00195 -0.0870 0.6511 1.0000 3.000 0.7281 0.00699 0.00212 -0.0859 0.5999 1.0000 3.500 0.7780 0.00749 0.00236 -0.0845 0.5356 1.0000 4.000 0.8270 0.00813 0.00272 -0.0831 0.4633 1.0000 4.500 0.8744 0.00895 0.00318 -0.0815 0.3807 1.0000 5.000 0.9213 0.00988 0.00374 -0.0800 0.3027 1.0000 5.500 0.9685 0.01081 0.00439 -0.0786 0.2363 1.0000 6.000 1.0158 0.01173 0.00509 -0.0772 0.1838 1.0000 6.500 1.0631 0.01264 0.00586 -0.0759 0.1466 1.0000 7.000 1.1100 0.01354 0.00668 -0.0744 0.1187 1.0000 7.500 1.1556 0.01456 0.00762 -0.0728 0.0960 1.0000 8.000 1.2010 0.01553 0.00862 -0.0712 0.0770 1.0000 8.500 1.2445 0.01663 0.00971 -0.0693 0.0596 1.0000 9.000 1.2856 0.01790 0.01101 -0.0671 0.0472 1.0000 9.500 1.3232 0.01939 0.01261 -0.0643 0.0382 1.0000 10.000 1.3542 0.02129 0.01459 -0.0608 0.0303 1.0000 10.500 1.3887 0.02263 0.01609 -0.0577 0.0257 1.0000 11.000 1.3993 0.02536 0.01900 -0.0513 0.0217 1.0000 11.500 1.4226 0.02717 0.02104 -0.0471 0.0190 1.0000 12.000 1.4358 0.02977 0.02378 -0.0425 0.0166 1.0000 12.500 1.4291 0.03452 0.02885 -0.0371 0.0153 1.0000 13.000 1.4371 0.03823 0.03286 -0.0340 0.0144 1.0000 13.500 1.4384 0.04295 0.03787 -0.0317 0.0134 1.0000 14.000 1.4355 0.04854 0.04373 -0.0307 0.0126 1.0000 14.500 1.4294 0.05511 0.05055 -0.0312 0.0119 1.0000 15.000 1.4109 0.06424 0.05996 -0.0335 0.0114 1.0000 15.500 1.3799 0.07655 0.07263 -0.0383 0.0110 1.0000 16.000 1.3441 0.09139 0.08785 -0.0457 0.0108 1.0000 16.500 1.3062 0.10822 0.10505 -0.0553 0.0107 1.0000 17.000 1.2712 0.12587 0.12303 -0.0660 0.0107 1.0000 17.500 1.2393 0.14404 0.14145 -0.0774 0.0108 1.0000 18.000 1.2071 0.16351 0.16117 -0.0898 0.0110 1.0000