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 = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.2475 0.05122 0.04006 -0.0291 1.0000 0.3766 -2.750 -0.2142 0.04905 0.03733 -0.0334 1.0000 0.3691 -2.500 -0.1798 0.04731 0.03491 -0.0374 1.0000 0.3649 -2.250 -0.1494 0.04580 0.03283 -0.0397 1.0000 0.3652 -2.000 -0.1230 0.04449 0.03121 -0.0407 1.0000 0.3738 -1.750 -0.0947 0.04343 0.02976 -0.0421 1.0000 0.3872 -1.500 -0.0660 0.04254 0.02848 -0.0435 1.0000 0.4022 -1.250 -0.0370 0.04173 0.02732 -0.0447 1.0000 0.4183 -1.000 -0.0090 0.04090 0.02643 -0.0455 1.0000 0.4418 -0.750 0.0190 0.04001 0.02566 -0.0461 1.0000 0.4834 -0.500 0.0442 0.03823 0.02506 -0.0455 1.0000 0.6009 -0.250 0.0744 0.03717 0.02334 -0.0466 1.0000 1.0000 0.000 0.0970 0.03800 0.02297 -0.0462 1.0000 1.0000 0.250 0.1157 0.03882 0.02312 -0.0457 1.0000 1.0000 0.500 0.1335 0.03969 0.02350 -0.0453 1.0000 1.0000 0.750 0.1510 0.04058 0.02401 -0.0450 1.0000 1.0000 1.000 0.1681 0.04152 0.02462 -0.0447 1.0000 1.0000 1.250 0.1852 0.04250 0.02531 -0.0445 1.0000 1.0000 1.500 0.2020 0.04351 0.02606 -0.0443 1.0000 1.0000 1.750 0.2186 0.04457 0.02690 -0.0441 1.0000 1.0000 2.000 0.2352 0.04565 0.02781 -0.0440 1.0000 1.0000 2.250 0.2515 0.04678 0.02878 -0.0439 1.0000 1.0000 2.500 0.2678 0.04795 0.02982 -0.0438 1.0000 1.0000 2.750 0.2838 0.04916 0.03093 -0.0438 1.0000 1.0000 3.000 0.2997 0.05041 0.03209 -0.0438 1.0000 1.0000 3.250 0.3154 0.05171 0.03332 -0.0438 1.0000 1.0000 3.500 0.3310 0.05304 0.03461 -0.0438 1.0000 1.0000 3.750 0.3463 0.05443 0.03600 -0.0439 1.0000 1.0000 4.000 0.3615 0.05587 0.03743 -0.0440 1.0000 1.0000 4.250 0.3764 0.05736 0.03893 -0.0441 1.0000 1.0000 4.500 0.3910 0.05890 0.04051 -0.0443 1.0000 1.0000 4.750 0.4054 0.06051 0.04217 -0.0445 1.0000 1.0000 5.000 0.4194 0.06219 0.04394 -0.0447 1.0000 1.0000