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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0053 0.04656 0.03837 -0.0585 0.8363 0.2496 -2.750 0.0339 0.04406 0.03572 -0.0591 0.8319 0.2428 -2.500 0.0763 0.04242 0.03334 -0.0613 0.8281 0.2321 -2.250 0.0858 0.04132 0.03210 -0.0586 0.8215 0.2308 -2.000 0.1115 0.04004 0.03044 -0.0579 0.8151 0.2320 -1.750 0.1452 0.03810 0.02843 -0.0587 0.8107 0.2451 -1.500 0.1804 0.03648 0.02654 -0.0595 0.8062 0.2567 -1.250 0.1941 0.03606 0.02582 -0.0571 0.7988 0.2693 -1.000 0.2381 0.03411 0.02377 -0.0593 0.7932 0.3038 -0.750 0.3099 0.03178 0.02135 -0.0657 0.7878 0.3723 -0.500 0.3338 0.03127 0.02098 -0.0652 0.7776 0.4083 -0.250 0.3857 0.02991 0.01981 -0.0683 0.7707 0.4489 0.000 0.4163 0.02923 0.01948 -0.0685 0.7626 0.4920 0.250 0.5318 0.02709 0.01826 -0.0834 0.7530 1.0000 0.500 0.5651 0.02705 0.01795 -0.0834 0.7436 1.0000 0.750 0.5961 0.02694 0.01762 -0.0829 0.7312 1.0000 1.000 0.6229 0.02694 0.01746 -0.0818 0.7169 1.0000 1.250 0.6609 0.02655 0.01689 -0.0821 0.7043 1.0000 1.500 0.6916 0.02642 0.01663 -0.0815 0.6884 1.0000 1.750 0.7184 0.02648 0.01658 -0.0803 0.6701 1.0000 2.000 0.7465 0.02655 0.01653 -0.0794 0.6508 1.0000 2.250 0.7737 0.02678 0.01663 -0.0784 0.6309 1.0000 2.500 0.7989 0.02722 0.01697 -0.0774 0.6118 1.0000 2.750 0.8229 0.02782 0.01749 -0.0764 0.5943 1.0000 3.000 0.8500 0.02828 0.01784 -0.0758 0.5793 1.0000 3.250 0.8700 0.02905 0.01857 -0.0744 0.5643 1.0000 3.500 0.8858 0.02999 0.01954 -0.0725 0.5501 1.0000 3.750 0.9127 0.03023 0.01968 -0.0717 0.5379 1.0000 4.000 0.9272 0.03105 0.02053 -0.0696 0.5239 1.0000 4.250 0.9447 0.03176 0.02126 -0.0679 0.5119 1.0000 4.500 0.9708 0.03176 0.02122 -0.0668 0.4996 1.0000 4.750 0.9808 0.03273 0.02228 -0.0643 0.4862 1.0000 5.000 1.0014 0.03297 0.02251 -0.0626 0.4735 1.0000