XFOIL Version 6.94 Calculated polar for: wouaibair3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.2592 0.04101 0.02720 -0.0588 0.4570 0.3780 -2.750 0.2949 0.04161 0.02762 -0.0600 0.4402 0.3932 -2.500 0.3390 0.04221 0.02809 -0.0630 0.4272 0.4221 -2.250 0.3822 0.04259 0.02868 -0.0658 0.4171 0.4532 -2.000 0.4296 0.04330 0.02946 -0.0696 0.4049 0.4922 -1.750 0.4730 0.04388 0.03030 -0.0725 0.3953 0.5292 -1.500 0.5167 0.04450 0.03128 -0.0752 0.3903 0.5722 -1.250 0.5588 0.04519 0.03236 -0.0775 0.3872 0.6204 -1.000 0.5948 0.04576 0.03347 -0.0780 0.3855 0.6825 -0.750 0.6330 0.04633 0.03445 -0.0794 0.3835 0.7334 -0.500 0.6720 0.04701 0.03546 -0.0816 0.3793 0.7707 -0.250 0.6998 0.04692 0.03609 -0.0810 0.3760 0.8500 0.000 0.7589 0.04867 0.03768 -0.0895 0.3771 1.0024 0.250 0.8015 0.05097 0.03982 -0.0934 0.3769 1.0024 0.500 0.8346 0.05323 0.04210 -0.0951 0.3742 1.0024 0.750 0.8669 0.05588 0.04486 -0.0966 0.3767 1.0024 1.000 0.8967 0.05876 0.04785 -0.0978 0.3784 1.0024 1.250 0.9237 0.06185 0.05108 -0.0985 0.3796 1.0024 1.500 0.9496 0.06431 0.05408 -0.1000 0.3946 1.0024 1.750 0.9741 0.06753 0.05773 -0.1018 0.4140 1.0024 2.000 0.9933 0.07113 0.06175 -0.1036 0.4353 1.0024 2.250 1.0044 0.07545 0.06650 -0.1059 0.4644 1.0024 2.500 0.9878 0.08097 0.07253 -0.1079 0.5093 1.0024 2.750 0.9131 0.08997 0.08184 -0.1067 0.5629 1.0024 3.000 0.7487 0.10668 0.09863 -0.1059 0.6683 1.0024 3.250 0.5355 0.11898 0.11128 -0.0910 0.9149 1.0024 3.500 0.5151 0.12348 0.11567 -0.0872 0.9637 1.0024 3.750 0.4974 0.12473 0.11684 -0.0826 0.9826 1.0024 4.000 0.4918 0.12736 0.11935 -0.0803 0.9951 1.0024 4.250 0.5008 0.13124 0.12311 -0.0814 0.9976 1.0024 4.500 0.5123 0.13498 0.12675 -0.0832 0.9976 1.0024 4.750 0.5538 0.14171 0.13335 -0.0920 0.9768 1.0024 5.000 0.5844 0.14457 0.13614 -0.0975 0.9366 1.0024