XFOIL Version 6.94 Calculated polar for: fauvel bl2 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 -0.0937 0.04128 0.03144 -0.0268 0.9995 0.4149 -2.750 -0.0688 0.04068 0.03075 -0.0274 0.9995 0.4318 -2.500 -0.0426 0.04031 0.03027 -0.0283 0.9995 0.4520 -2.250 -0.0169 0.04002 0.03007 -0.0289 0.9995 0.4780 -2.000 0.0083 0.03978 0.03009 -0.0294 0.9995 0.5104 -1.750 0.2370 0.03277 0.02353 -0.0581 0.8962 1.0005 -1.500 0.2748 0.03391 0.02424 -0.0548 0.8149 1.0005 -1.250 0.2838 0.03594 0.02590 -0.0464 0.7370 1.0005 -1.000 0.2958 0.03799 0.02751 -0.0401 0.6673 1.0005 -0.750 0.3185 0.03970 0.02889 -0.0382 0.6127 1.0005 -0.500 0.3424 0.04075 0.02960 -0.0361 0.5794 1.0005 -0.250 0.3707 0.04204 0.03063 -0.0361 0.5530 1.0005 0.000 0.3983 0.04315 0.03148 -0.0356 0.5334 1.0005 0.250 0.4282 0.04469 0.03287 -0.0368 0.5142 1.0005 0.500 0.4578 0.04659 0.03466 -0.0386 0.4979 1.0005 0.750 0.4846 0.04774 0.03556 -0.0379 0.4874 1.0005 1.000 0.5154 0.05118 0.03905 -0.0426 0.4773 1.0005 1.250 0.5420 0.05286 0.04057 -0.0427 0.4695 1.0005 1.500 0.5679 0.05641 0.04411 -0.0463 0.4622 1.0005 1.750 0.5900 0.06054 0.04828 -0.0506 0.4559 1.0005 2.000 0.6097 0.06453 0.05227 -0.0539 0.4524 1.0005 2.250 0.6221 0.07000 0.05779 -0.0588 0.4535 1.0005 2.500 0.6270 0.07593 0.06374 -0.0635 0.4571 1.0005 2.750 0.6315 0.08116 0.06896 -0.0668 0.4608 1.0005 3.000 0.6386 0.08582 0.07358 -0.0690 0.4640 1.0005 3.250 0.6465 0.09041 0.07814 -0.0710 0.4679 1.0005 3.500 0.5879 0.09881 0.08660 -0.0753 0.5001 1.0005 3.750 0.5912 0.10532 0.09309 -0.0794 0.5324 1.0005