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 = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1268 0.04464 0.03473 -0.0380 0.9995 0.2883 -2.750 0.1809 0.03589 0.02582 -0.0777 0.8409 0.3782 -2.500 0.2006 0.03487 0.02486 -0.0717 0.8020 0.4020 -2.250 0.2168 0.03341 0.02366 -0.0652 0.7621 0.4398 -2.000 0.2349 0.03083 0.02208 -0.0604 0.7181 0.5465 -1.500 0.2829 0.02704 0.01739 -0.0517 0.4646 1.0005 -1.250 0.3065 0.02803 0.01756 -0.0506 0.4382 1.0005 -1.000 0.3315 0.02887 0.01783 -0.0497 0.4210 1.0005 -0.750 0.3572 0.02964 0.01813 -0.0487 0.4082 1.0005 -0.500 0.3847 0.03032 0.01845 -0.0479 0.3996 1.0005 -0.250 0.4133 0.03097 0.01884 -0.0474 0.3912 1.0005 0.000 0.4418 0.03179 0.01934 -0.0468 0.3830 1.0005 0.250 0.4714 0.03272 0.01998 -0.0464 0.3761 1.0005 0.500 0.5019 0.03347 0.02064 -0.0464 0.3701 1.0005 0.750 0.5326 0.03435 0.02140 -0.0464 0.3658 1.0005 1.000 0.5634 0.03534 0.02228 -0.0465 0.3622 1.0005 1.250 0.5940 0.03649 0.02330 -0.0466 0.3584 1.0005 1.500 0.6241 0.03792 0.02457 -0.0467 0.3545 1.0005 1.750 0.6544 0.03941 0.02599 -0.0471 0.3512 1.0005 2.000 0.6850 0.04062 0.02730 -0.0478 0.3486 1.0005 2.250 0.7155 0.04206 0.02883 -0.0486 0.3474 1.0005 2.500 0.7457 0.04365 0.03052 -0.0494 0.3469 1.0005 2.750 0.7753 0.04540 0.03239 -0.0503 0.3468 1.0005 3.000 0.8043 0.04727 0.03441 -0.0512 0.3464 1.0005 3.250 0.8322 0.04928 0.03658 -0.0523 0.3457 1.0005 3.500 0.8588 0.05149 0.03897 -0.0533 0.3453 1.0005 3.750 0.8844 0.05399 0.04167 -0.0544 0.3462 1.0005 4.000 0.9089 0.05687 0.04472 -0.0555 0.3486 1.0005 4.250 0.9328 0.06016 0.04810 -0.0565 0.3512 1.0005 4.500 0.9456 0.06349 0.05210 -0.0591 0.3592 1.0005 4.750 0.9433 0.06956 0.05865 -0.0617 0.3698 1.0005 5.000 0.9555 0.07451 0.06369 -0.0630 0.3759 1.0005