XFOIL Version 6.94 Calculated polar for: Eiffel 430 (Lachassgne) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.2401 0.05225 0.04670 0.0079 0.8833 0.6552 -2.750 -0.0691 0.04964 0.04178 -0.0451 0.8714 0.3023 -2.500 -0.0205 0.04775 0.03912 -0.0496 0.8658 0.2673 -2.250 -0.0047 0.04625 0.03743 -0.0481 0.8602 0.2619 -2.000 0.0283 0.04520 0.03571 -0.0489 0.8543 0.2504 -1.750 0.0677 0.04293 0.03328 -0.0508 0.8484 0.2555 -1.500 0.0883 0.04197 0.03211 -0.0496 0.8421 0.2639 -1.250 0.1165 0.04092 0.03066 -0.0495 0.8358 0.2712 -1.000 0.1555 0.03948 0.02895 -0.0509 0.8302 0.2913 -0.750 0.2019 0.03803 0.02728 -0.0539 0.8243 0.3258 -0.500 0.2424 0.03697 0.02612 -0.0559 0.8155 0.3743 -0.250 0.3137 0.03500 0.02448 -0.0624 0.8077 0.4451 0.000 0.3327 0.03481 0.02450 -0.0612 0.7975 0.4788 0.250 0.4672 0.03187 0.02278 -0.0785 0.7864 1.0000 0.500 0.4949 0.03203 0.02264 -0.0777 0.7724 1.0000 0.750 0.5255 0.03209 0.02244 -0.0773 0.7584 1.0000 1.000 0.5719 0.03154 0.02166 -0.0788 0.7449 1.0000 1.250 0.6088 0.03124 0.02122 -0.0789 0.7294 1.0000 1.500 0.6386 0.03119 0.02104 -0.0782 0.7114 1.0000 1.750 0.6718 0.03105 0.02079 -0.0778 0.6926 1.0000 2.000 0.7059 0.03092 0.02055 -0.0775 0.6729 1.0000 2.250 0.7381 0.03098 0.02050 -0.0770 0.6528 1.0000 2.500 0.7665 0.03136 0.02077 -0.0763 0.6336 1.0000 2.750 0.7932 0.03198 0.02131 -0.0757 0.6169 1.0000 3.000 0.8261 0.03240 0.02163 -0.0759 0.6040 1.0000 3.250 0.8335 0.03415 0.02340 -0.0735 0.5890 1.0000 3.500 0.8561 0.03506 0.02426 -0.0726 0.5777 1.0000 4.000 0.8830 0.03762 0.02686 -0.0689 0.5534 1.0000 4.250 0.9193 0.03716 0.02634 -0.0686 0.5408 1.0000 4.500 0.9122 0.03968 0.02894 -0.0650 0.5291 1.0000 4.750 0.9455 0.03918 0.02843 -0.0643 0.5159 1.0000 5.000 0.9645 0.03942 0.02868 -0.0623 0.5012 1.0000