XFOIL Version 6.94 Calculated polar for: FAUVEL BL 1 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 -0.1482 0.04896 0.03828 -0.0323 0.9995 0.3924 -2.750 -0.1164 0.04776 0.03699 -0.0331 0.9995 0.4102 -2.500 -0.0829 0.04680 0.03586 -0.0343 0.9995 0.4297 -2.250 -0.0503 0.04597 0.03502 -0.0350 0.9995 0.4544 -2.000 -0.0180 0.04511 0.03435 -0.0354 0.9995 0.4836 -1.750 0.0141 0.04417 0.03387 -0.0355 0.9995 0.5301 -1.500 0.0448 0.04269 0.03354 -0.0347 0.9995 0.6279 -1.250 0.3415 0.03626 0.02587 -0.0705 0.8079 1.0005 -1.000 0.3686 0.03570 0.02509 -0.0663 0.7564 1.0005 -0.750 0.3849 0.03537 0.02481 -0.0639 0.6903 1.0005 -0.500 0.3975 0.03618 0.02572 -0.0636 0.5890 1.0005 -0.250 0.4402 0.03355 0.02226 -0.0591 0.5442 1.0005 0.000 0.4662 0.03288 0.02035 -0.0542 0.5196 1.0005 0.250 0.4913 0.03368 0.02032 -0.0522 0.5007 1.0005 0.500 0.5194 0.03469 0.02094 -0.0516 0.4877 1.0005 0.750 0.5479 0.03586 0.02165 -0.0510 0.4778 1.0005 1.000 0.5778 0.03703 0.02271 -0.0513 0.4685 1.0005 1.250 0.6073 0.03840 0.02382 -0.0513 0.4594 1.0005 1.500 0.6374 0.03986 0.02514 -0.0516 0.4522 1.0005 1.750 0.6678 0.04128 0.02662 -0.0524 0.4470 1.0005 2.000 0.6983 0.04284 0.02824 -0.0534 0.4435 1.0005 2.250 0.7284 0.04458 0.03005 -0.0544 0.4402 1.0005 2.500 0.7577 0.04652 0.03203 -0.0553 0.4365 1.0005 2.750 0.7862 0.04869 0.03421 -0.0561 0.4327 1.0005 3.000 0.8136 0.05116 0.03672 -0.0571 0.4298 1.0005 3.250 0.8387 0.05382 0.03961 -0.0587 0.4290 1.0005 3.500 0.8629 0.05682 0.04280 -0.0604 0.4296 1.0005 3.750 0.8809 0.06048 0.04680 -0.0626 0.4316 1.0005 4.000 0.8600 0.06868 0.05567 -0.0671 0.4404 1.0005 4.250 0.8318 0.07782 0.06507 -0.0704 0.4505 1.0005 4.500 0.8322 0.08384 0.07114 -0.0723 0.4560 1.0005 5.000 0.6352 0.11415 0.10165 -0.0842 0.5545 1.0005