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 = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1315 0.04591 0.03576 -0.0371 0.9995 0.3165 -2.750 -0.1035 0.04485 0.03481 -0.0370 0.9995 0.3328 -2.500 -0.0713 0.04406 0.03389 -0.0376 0.9995 0.3484 -2.250 0.2292 0.03480 0.02548 -0.0743 0.8281 0.5184 -2.000 0.2535 0.03160 0.02343 -0.0664 0.7850 1.0005 -1.750 0.2745 0.03077 0.02201 -0.0610 0.7409 1.0005 -1.500 0.3008 0.03015 0.02137 -0.0615 0.6720 1.0005 -1.250 0.3219 0.02831 0.01855 -0.0550 0.5065 1.0005 -1.000 0.3412 0.02884 0.01790 -0.0515 0.4710 1.0005 -0.750 0.3646 0.02982 0.01819 -0.0501 0.4503 1.0005 -0.500 0.3902 0.03071 0.01859 -0.0492 0.4351 1.0005 -0.250 0.4176 0.03152 0.01901 -0.0484 0.4253 1.0005 0.000 0.4463 0.03228 0.01952 -0.0480 0.4163 1.0005 0.250 0.4750 0.03326 0.02015 -0.0475 0.4078 1.0005 0.500 0.5049 0.03422 0.02089 -0.0473 0.4005 1.0005 0.750 0.5354 0.03511 0.02170 -0.0474 0.3936 1.0005 1.000 0.5663 0.03613 0.02261 -0.0475 0.3886 1.0005 1.250 0.5972 0.03728 0.02365 -0.0477 0.3849 1.0005 1.500 0.6278 0.03864 0.02488 -0.0479 0.3813 1.0005 1.750 0.6582 0.04023 0.02636 -0.0482 0.3779 1.0005 2.000 0.6888 0.04146 0.02772 -0.0490 0.3747 1.0005 2.250 0.7190 0.04288 0.02925 -0.0498 0.3718 1.0005 2.500 0.7489 0.04449 0.03097 -0.0507 0.3703 1.0005 2.750 0.7785 0.04628 0.03289 -0.0517 0.3700 1.0005 3.000 0.8074 0.04826 0.03503 -0.0528 0.3702 1.0005 3.250 0.8351 0.05042 0.03737 -0.0540 0.3702 1.0005 3.500 0.8613 0.05281 0.03994 -0.0552 0.3699 1.0005 3.750 0.8856 0.05545 0.04278 -0.0564 0.3699 1.0005 4.000 0.9075 0.05849 0.04605 -0.0578 0.3713 1.0005 4.250 0.9277 0.06200 0.04974 -0.0591 0.3745 1.0005 4.500 0.9492 0.06580 0.05361 -0.0602 0.3777 1.0005 4.750 0.9067 0.07549 0.06424 -0.0653 0.3973 1.0005 5.000 0.9146 0.08104 0.06988 -0.0672 0.4062 1.0005