XFOIL Version 6.94 Calculated polar for: BL BAP 04 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 -0.1982 0.05709 0.04663 -0.0312 0.9998 0.3876 -2.750 -0.1587 0.05488 0.04416 -0.0355 0.9998 0.3843 -2.500 -0.1188 0.05298 0.04200 -0.0396 0.9998 0.3818 -2.250 -0.0791 0.05139 0.04014 -0.0433 0.9998 0.3800 -2.000 -0.0405 0.05011 0.03862 -0.0466 0.9998 0.3795 -1.750 -0.0042 0.04913 0.03746 -0.0493 0.9998 0.3814 -1.500 0.0292 0.04853 0.03674 -0.0516 0.9998 0.3863 -1.250 0.0574 0.04857 0.03671 -0.0536 0.9998 0.3942 -1.000 0.0930 0.04902 0.03733 -0.0582 0.9895 0.4076 -0.750 0.1623 0.04838 0.03680 -0.0688 0.9472 0.4401 -0.500 0.2097 0.04784 0.03664 -0.0745 0.9133 0.4872 -0.250 0.2389 0.04675 0.03691 -0.0758 0.8906 0.6093 0.000 0.2612 0.04709 0.03705 -0.0768 0.8708 1.0002 0.250 0.2926 0.04917 0.03802 -0.0793 0.8612 1.0002 0.500 0.3154 0.05142 0.03949 -0.0807 0.8552 1.0002 0.750 0.3369 0.05381 0.04129 -0.0822 0.8522 1.0002 1.000 0.3559 0.05632 0.04334 -0.0837 0.8504 1.0002 1.250 0.3725 0.05893 0.04558 -0.0848 0.8493 1.0002 1.500 0.3854 0.06165 0.04801 -0.0856 0.8493 1.0002 1.750 0.3922 0.06455 0.05068 -0.0855 0.8512 1.0002 2.000 0.3949 0.06760 0.05354 -0.0850 0.8564 1.0002 2.250 0.4045 0.07084 0.05657 -0.0858 0.8645 1.0002 2.500 0.3921 0.07398 0.05962 -0.0831 0.8777 1.0002 2.750 0.3950 0.07728 0.06278 -0.0829 0.8915 1.0002 3.000 0.3905 0.08052 0.06588 -0.0814 0.9097 1.0002 3.250 0.3811 0.08352 0.06877 -0.0788 0.9323 1.0002 3.500 0.3465 0.08510 0.07033 -0.0713 0.9695 1.0002 3.750 0.3149 0.08575 0.07093 -0.0631 0.9998 1.0002 4.000 0.3286 0.08821 0.07322 -0.0639 0.9998 1.0002 4.250 0.3421 0.09070 0.07556 -0.0647 0.9998 1.0002 4.500 0.3554 0.09323 0.07795 -0.0655 0.9998 1.0002 4.750 0.3687 0.09579 0.08039 -0.0664 0.9998 1.0002 5.000 0.3818 0.09839 0.08289 -0.0672 0.9998 1.0002