XFOIL Version 6.94 Calculated polar for: GD BAP 00 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 -0.1839 0.05788 0.04715 -0.0354 0.9998 0.3868 -2.750 -0.1341 0.05541 0.04422 -0.0435 0.9998 0.3811 -2.500 -0.0940 0.05307 0.04164 -0.0480 0.9998 0.3788 -2.250 -0.0543 0.05099 0.03938 -0.0519 0.9998 0.3768 -2.000 -0.0143 0.04929 0.03749 -0.0557 0.9998 0.3761 -1.750 0.0252 0.04795 0.03599 -0.0590 0.9998 0.3774 -1.500 0.0635 0.04695 0.03494 -0.0621 0.9998 0.3809 -1.250 0.0965 0.04609 0.03433 -0.0644 0.9998 0.3881 -1.000 0.1221 0.04634 0.03493 -0.0667 0.9998 0.3975 -0.750 0.1300 0.04908 0.03793 -0.0697 0.9953 0.4047 -0.500 0.2301 0.04801 0.03723 -0.0863 0.9273 0.4677 -0.250 0.2625 0.04718 0.03744 -0.0882 0.8859 0.5442 0.000 0.2865 0.04608 0.03675 -0.0868 0.8595 0.8518 0.250 0.3194 0.04583 0.03572 -0.0887 0.8355 1.0002 0.500 0.3535 0.04754 0.03649 -0.0913 0.8216 1.0002 0.750 0.3949 0.04906 0.03723 -0.0951 0.8116 1.0002 1.000 0.4132 0.05161 0.03939 -0.0967 0.8066 1.0002 1.250 0.4310 0.05434 0.04180 -0.0984 0.8042 1.0002 1.500 0.4462 0.05732 0.04451 -0.1000 0.8046 1.0002 1.750 0.4593 0.06049 0.04747 -0.1015 0.8073 1.0002 2.000 0.4748 0.06375 0.05051 -0.1033 0.8114 1.0002 2.250 0.4653 0.06757 0.05425 -0.1021 0.8200 1.0002 2.500 0.4624 0.07106 0.05763 -0.1015 0.8285 1.0002 2.750 0.4706 0.07426 0.06068 -0.1021 0.8335 1.0002 3.000 0.4819 0.07736 0.06363 -0.1031 0.8365 1.0002 3.250 0.4955 0.08055 0.06668 -0.1044 0.8395 1.0002 3.500 0.4772 0.08348 0.06959 -0.1014 0.8535 1.0002 3.750 0.4847 0.08701 0.07300 -0.1022 0.8655 1.0002 4.000 0.4710 0.08975 0.07571 -0.0997 0.8845 1.0002 4.250 0.4861 0.09390 0.07974 -0.1017 0.8989 1.0002 4.500 0.4515 0.09542 0.08128 -0.0954 0.9382 1.0002 4.750 0.4009 0.09583 0.08164 -0.0843 0.9998 1.0002 5.000 0.4145 0.09852 0.08423 -0.0853 0.9998 1.0002