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 = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.2263 0.04552 0.03681 -0.0388 1.0000 0.2460 -2.750 -0.1985 0.04344 0.03424 -0.0407 1.0000 0.2323 -2.500 -0.1693 0.04181 0.03189 -0.0425 1.0000 0.2213 -2.250 -0.1463 0.04052 0.03026 -0.0429 1.0000 0.2210 -2.000 -0.1250 0.03940 0.02886 -0.0430 1.0000 0.2238 -1.750 -0.1040 0.03851 0.02771 -0.0429 1.0000 0.2255 -1.500 -0.0817 0.03780 0.02662 -0.0429 1.0000 0.2247 -1.250 -0.0573 0.03729 0.02573 -0.0432 1.0000 0.2256 -1.000 -0.0325 0.03696 0.02505 -0.0435 1.0000 0.2282 -0.750 -0.0077 0.03678 0.02458 -0.0439 1.0000 0.2331 -0.500 0.0168 0.03678 0.02427 -0.0442 1.0000 0.2397 -0.250 0.0408 0.03673 0.02421 -0.0445 1.0000 0.2524 0.000 0.0648 0.03682 0.02431 -0.0450 1.0000 0.2772 0.250 0.0902 0.03675 0.02447 -0.0456 1.0000 0.3168 0.500 0.1176 0.03447 0.02423 -0.0461 1.0000 1.0000 0.750 0.1539 0.03600 0.02478 -0.0484 0.9926 1.0000 1.000 0.2036 0.03792 0.02618 -0.0539 0.9738 1.0000 1.250 0.2522 0.03980 0.02768 -0.0591 0.9558 1.0000 1.500 0.2809 0.04099 0.02869 -0.0608 0.9432 1.0000 1.750 0.3103 0.04232 0.02985 -0.0626 0.9316 1.0000 2.000 0.3477 0.04399 0.03137 -0.0657 0.9207 1.0000 2.250 0.3610 0.04503 0.03234 -0.0650 0.9155 1.0000 2.500 0.3927 0.04657 0.03381 -0.0671 0.9054 1.0000 2.750 0.4107 0.04779 0.03499 -0.0671 0.8969 1.0000 3.000 0.4440 0.04933 0.03651 -0.0692 0.8832 1.0000 3.250 0.4622 0.05062 0.03781 -0.0693 0.8749 1.0000 3.500 0.4877 0.05211 0.03930 -0.0703 0.8639 1.0000 3.750 0.5207 0.05371 0.04097 -0.0722 0.8502 1.0000 4.000 0.5375 0.05501 0.04232 -0.0719 0.8390 1.0000 4.250 0.5654 0.05638 0.04378 -0.0728 0.8221 1.0000 4.500 0.6080 0.05775 0.04527 -0.0752 0.8003 1.0000 4.750 0.6396 0.05900 0.04669 -0.0761 0.7815 1.0000 5.000 0.6534 0.06034 0.04815 -0.0752 0.7673 1.0000