XFOIL Version 6.94 Calculated polar for: Eiffel 428 (Bleriot) 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 ------- -------- --------- --------- -------- ------- ------- -2.750 -0.3617 0.04931 0.04387 0.0080 1.0000 0.5477 -2.500 -0.1752 0.04004 0.03121 -0.0420 1.0000 0.1957 -2.250 -0.1372 0.03855 0.02894 -0.0447 0.9957 0.1851 -2.000 -0.0957 0.03729 0.02730 -0.0481 0.9871 0.1817 -1.750 -0.0541 0.03670 0.02621 -0.0514 0.9783 0.1853 -1.500 -0.0120 0.03612 0.02538 -0.0547 0.9681 0.1899 -1.250 0.0376 0.03570 0.02462 -0.0588 0.9547 0.1927 -1.000 0.0953 0.03536 0.02391 -0.0640 0.9370 0.1997 -0.750 0.1519 0.03495 0.02337 -0.0688 0.9190 0.2140 -0.500 0.2061 0.03450 0.02302 -0.0732 0.9026 0.2517 -0.250 0.2633 0.03167 0.02226 -0.0780 0.8895 1.0000 0.000 0.2918 0.03241 0.02247 -0.0783 0.8781 1.0000 0.250 0.3323 0.03309 0.02276 -0.0806 0.8667 1.0000 0.500 0.3578 0.03382 0.02328 -0.0808 0.8556 1.0000 0.750 0.3832 0.03462 0.02390 -0.0810 0.8453 1.0000 1.000 0.4213 0.03529 0.02442 -0.0830 0.8357 1.0000 1.250 0.4355 0.03624 0.02526 -0.0817 0.8253 1.0000 1.500 0.4754 0.03684 0.02577 -0.0838 0.8156 1.0000 1.750 0.4888 0.03783 0.02671 -0.0824 0.8054 1.0000 2.000 0.5240 0.03862 0.02747 -0.0840 0.7984 1.0000 2.250 0.5279 0.03999 0.02880 -0.0817 0.7906 1.0000 2.500 0.5572 0.04094 0.02975 -0.0826 0.7841 1.0000 2.750 0.5692 0.04220 0.03102 -0.0813 0.7762 1.0000 3.000 0.5933 0.04320 0.03206 -0.0814 0.7679 1.0000 3.250 0.6129 0.04437 0.03327 -0.0810 0.7602 1.0000 3.500 0.6323 0.04544 0.03439 -0.0805 0.7508 1.0000 3.750 0.6528 0.04648 0.03549 -0.0800 0.7405 1.0000 4.000 0.6877 0.04709 0.03625 -0.0809 0.7302 1.0000 4.250 0.7002 0.04818 0.03742 -0.0793 0.7170 1.0000 4.500 0.7270 0.04874 0.03810 -0.0788 0.7027 1.0000 4.750 0.7707 0.04791 0.03750 -0.0787 0.6814 1.0000 5.000 0.8547 0.04375 0.03369 -0.0800 0.6552 1.0000