XFOIL Version 6.94 Calculated polar for: fauvel bl3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1113 0.04413 0.03372 -0.0300 0.9995 0.4052 -2.750 -0.0834 0.04333 0.03280 -0.0305 0.9995 0.4239 -2.500 -0.0549 0.04260 0.03204 -0.0311 0.9995 0.4434 -2.250 -0.0263 0.04202 0.03149 -0.0316 0.9995 0.4690 -2.000 0.0024 0.04148 0.03109 -0.0321 0.9995 0.5013 -1.750 0.0300 0.04080 0.03089 -0.0320 0.9995 0.5556 -1.500 0.0500 0.03913 0.03073 -0.0290 0.9995 0.7108 -1.250 0.0764 0.03868 0.02956 -0.0302 0.9995 1.0005 -1.000 0.3500 0.03562 0.02527 -0.0614 0.8071 1.0005 -0.750 0.3622 0.03670 0.02610 -0.0531 0.7268 1.0005 -0.500 0.3771 0.03762 0.02670 -0.0473 0.6536 1.0005 -0.250 0.3992 0.03791 0.02666 -0.0441 0.6031 1.0005 0.000 0.4259 0.03832 0.02680 -0.0429 0.5645 1.0005 0.250 0.4526 0.03864 0.02681 -0.0414 0.5407 1.0005 0.500 0.4804 0.03921 0.02711 -0.0406 0.5204 1.0005 0.750 0.5085 0.04001 0.02767 -0.0403 0.5024 1.0005 1.000 0.5366 0.04094 0.02838 -0.0401 0.4872 1.0005 1.250 0.5638 0.04147 0.02859 -0.0389 0.4760 1.0005 1.500 0.5934 0.04367 0.03080 -0.0410 0.4658 1.0005 1.750 0.6213 0.04469 0.03159 -0.0404 0.4590 1.0005 2.000 0.6494 0.04802 0.03504 -0.0439 0.4515 1.0005 2.250 0.6760 0.05024 0.03721 -0.0450 0.4447 1.0005 2.500 0.7021 0.05219 0.03905 -0.0455 0.4389 1.0005 2.750 0.7205 0.05761 0.04469 -0.0504 0.4356 1.0005 3.000 0.7313 0.06398 0.05122 -0.0553 0.4361 1.0005 3.250 0.7375 0.07038 0.05771 -0.0595 0.4383 1.0005 3.750 0.6956 0.08889 0.07641 -0.0708 0.4560 1.0005 4.250 0.6310 0.10401 0.09153 -0.0759 0.4892 1.0005