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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.4454 0.06001 0.05424 0.0643 1.0000 0.7555 -2.750 -0.4721 0.05746 0.05167 0.0630 1.0000 0.7138 -2.500 -0.3502 0.05552 0.04836 0.0135 1.0000 0.4792 -2.250 -0.2893 0.05345 0.04553 0.0009 1.0000 0.3892 -2.000 -0.2492 0.05192 0.04339 -0.0045 1.0000 0.3510 -1.750 -0.2091 0.05033 0.04132 -0.0085 0.9962 0.3294 -1.500 -0.1602 0.04913 0.03948 -0.0136 0.9883 0.3101 -1.250 -0.1174 0.04777 0.03778 -0.0170 0.9794 0.3078 -1.000 -0.0776 0.04677 0.03634 -0.0197 0.9691 0.3119 -0.750 -0.0271 0.04564 0.03477 -0.0241 0.9562 0.3188 -0.500 0.0291 0.04490 0.03355 -0.0293 0.9446 0.3415 -0.250 0.0743 0.04402 0.03234 -0.0327 0.9344 0.3688 0.000 0.1340 0.04307 0.03140 -0.0384 0.9212 0.4320 0.250 0.1963 0.04219 0.03103 -0.0445 0.9061 0.5183 0.500 0.2874 0.04106 0.03114 -0.0561 0.8871 1.0000 0.750 0.3338 0.04183 0.03134 -0.0591 0.8636 1.0000 1.000 0.3757 0.04255 0.03166 -0.0613 0.8389 1.0000 1.250 0.4271 0.04314 0.03194 -0.0646 0.8113 1.0000 1.500 0.4685 0.04369 0.03227 -0.0663 0.7820 1.0000 1.750 0.5092 0.04431 0.03271 -0.0679 0.7532 1.0000 2.000 0.5522 0.04501 0.03327 -0.0698 0.7295 1.0000 2.250 0.5811 0.04619 0.03432 -0.0702 0.7088 1.0000 2.500 0.5919 0.04812 0.03614 -0.0690 0.6910 1.0000 2.750 0.6004 0.05024 0.03816 -0.0677 0.6767 1.0000 3.000 0.6431 0.05095 0.03880 -0.0694 0.6659 1.0000 3.250 0.6218 0.05445 0.04222 -0.0659 0.6544 1.0000 3.500 0.6508 0.05589 0.04362 -0.0665 0.6462 1.0000 3.750 0.6403 0.05929 0.04695 -0.0646 0.6407 1.0000 4.000 0.6314 0.06260 0.05021 -0.0631 0.6369 1.0000 4.250 0.6310 0.06553 0.05311 -0.0623 0.6332 1.0000 4.500 0.6426 0.06798 0.05554 -0.0620 0.6282 1.0000 4.750 0.6611 0.07034 0.05790 -0.0622 0.6227 1.0000 5.000 0.6563 0.07368 0.06123 -0.0615 0.6221 1.0000