XFOIL Version 6.94 Calculated polar for: GD BAP 01 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.018 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1836 0.05569 0.04387 -0.0289 0.9998 0.3806 -2.750 -0.1475 0.05344 0.04144 -0.0320 0.9998 0.3765 -2.500 -0.1100 0.05156 0.03932 -0.0352 0.9998 0.3743 -2.250 -0.0724 0.04999 0.03752 -0.0382 0.9998 0.3754 -2.000 -0.0350 0.04870 0.03598 -0.0409 0.9998 0.3791 -1.750 0.0017 0.04757 0.03473 -0.0434 0.9998 0.3843 -1.500 0.0355 0.04645 0.03373 -0.0452 0.9998 0.3923 -1.250 0.0684 0.04585 0.03331 -0.0472 0.9998 0.4020 -1.000 0.0949 0.04619 0.03387 -0.0495 0.9998 0.4122 -0.750 0.0961 0.04908 0.03695 -0.0509 0.9998 0.4173 -0.500 0.1987 0.04748 0.03600 -0.0682 0.9281 0.4868 -0.250 0.2328 0.04558 0.03587 -0.0698 0.8921 0.6677 0.000 0.2699 0.04622 0.03559 -0.0738 0.8620 1.0002 0.250 0.3100 0.04779 0.03601 -0.0772 0.8441 1.0002 0.500 0.3468 0.04942 0.03683 -0.0804 0.8312 1.0002 0.750 0.3711 0.05153 0.03844 -0.0823 0.8228 1.0002 1.000 0.3937 0.05373 0.04024 -0.0841 0.8153 1.0002 1.250 0.4326 0.05533 0.04140 -0.0879 0.8064 1.0002 1.500 0.4426 0.05816 0.04402 -0.0882 0.8026 1.0002 1.750 0.4538 0.06110 0.04675 -0.0889 0.8012 1.0002 2.000 0.4656 0.06430 0.04977 -0.0900 0.8041 1.0002 2.250 0.4584 0.06814 0.05352 -0.0888 0.8123 1.0002 2.500 0.4554 0.07184 0.05710 -0.0882 0.8226 1.0002 2.750 0.4522 0.07538 0.06055 -0.0875 0.8335 1.0002 3.000 0.4479 0.07883 0.06389 -0.0865 0.8458 1.0002 3.250 0.4403 0.08202 0.06701 -0.0849 0.8593 1.0002 3.500 0.4441 0.08528 0.07016 -0.0848 0.8703 1.0002 3.750 0.4365 0.08803 0.07285 -0.0829 0.8839 1.0002 4.000 0.4427 0.09115 0.07585 -0.0830 0.8935 1.0002 4.250 0.4339 0.09362 0.07826 -0.0807 0.9109 1.0002 5.000 0.3815 0.09887 0.08331 -0.0666 0.9998 1.0002