XFOIL Version 6.94 Calculated polar for: FAUVEL BL 1 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 -0.1617 0.05079 0.03978 -0.0277 0.9995 0.4435 -2.750 -0.1284 0.04944 0.03829 -0.0291 0.9995 0.4630 -2.500 -0.0954 0.04830 0.03707 -0.0302 0.9995 0.4871 -2.250 -0.0631 0.04724 0.03608 -0.0309 0.9995 0.5156 -2.000 -0.0316 0.04621 0.03530 -0.0312 0.9995 0.5565 -1.750 -0.0013 0.04495 0.03467 -0.0307 0.9995 0.6217 -1.500 0.0145 0.04226 0.03372 -0.0255 0.9995 0.8756 -1.250 0.0655 0.04222 0.03197 -0.0321 0.9995 1.0005 -1.000 0.0955 0.04277 0.03217 -0.0327 0.9995 1.0005 -0.750 0.3910 0.04002 0.02858 -0.0711 0.7941 1.0005 -0.500 0.4149 0.03989 0.02835 -0.0677 0.7289 1.0005 -0.250 0.4285 0.04050 0.02892 -0.0661 0.6584 1.0005 0.000 0.4556 0.04085 0.02906 -0.0656 0.6095 1.0005 0.250 0.4888 0.04034 0.02825 -0.0644 0.5780 1.0005 0.500 0.5251 0.03892 0.02632 -0.0617 0.5563 1.0005 0.750 0.5575 0.03816 0.02480 -0.0588 0.5399 1.0005 1.000 0.5872 0.03867 0.02478 -0.0575 0.5274 1.0005 1.250 0.6168 0.03966 0.02534 -0.0569 0.5171 1.0005 1.500 0.6460 0.04102 0.02643 -0.0569 0.5070 1.0005 1.750 0.6751 0.04259 0.02775 -0.0571 0.4982 1.0005 2.000 0.7030 0.04455 0.02973 -0.0581 0.4906 1.0005 2.250 0.7313 0.04655 0.03171 -0.0590 0.4852 1.0005 2.500 0.7593 0.04880 0.03397 -0.0601 0.4820 1.0005 2.750 0.7865 0.05131 0.03648 -0.0613 0.4791 1.0005 3.000 0.8065 0.05494 0.04040 -0.0637 0.4773 1.0005 3.250 0.8199 0.05939 0.04510 -0.0661 0.4762 1.0005 3.500 0.8249 0.06482 0.05076 -0.0685 0.4766 1.0005 3.750 0.8254 0.07078 0.05686 -0.0708 0.4788 1.0005 4.500 0.6528 0.10454 0.09092 -0.0809 0.5369 1.0005 4.750 0.6234 0.11154 0.09793 -0.0828 0.5622 1.0005 5.000 0.5904 0.11842 0.10484 -0.0848 0.6012 1.0005