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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1737 0.05342 0.04264 -0.0321 0.9998 0.3395 -2.750 -0.1377 0.05120 0.04024 -0.0351 0.9998 0.3329 -2.500 -0.0995 0.04936 0.03812 -0.0382 0.9998 0.3269 -2.250 -0.0612 0.04783 0.03630 -0.0412 0.9998 0.3225 -2.000 -0.0234 0.04658 0.03478 -0.0438 0.9998 0.3203 -1.750 0.0133 0.04555 0.03364 -0.0460 0.9998 0.3204 -1.500 0.0477 0.04485 0.03300 -0.0482 0.9998 0.3245 -1.250 0.0747 0.04507 0.03344 -0.0505 0.9998 0.3305 -1.000 0.1886 0.04222 0.03058 -0.0694 0.8981 0.3543 -0.750 0.2215 0.04169 0.03010 -0.0721 0.8299 0.3705 -0.500 0.2757 0.04025 0.02888 -0.0771 0.7948 0.4081 -0.250 0.3209 0.03588 0.02679 -0.0781 0.7749 1.0002 0.000 0.4092 0.03511 0.02396 -0.0860 0.7555 1.0002 0.250 0.4899 0.03461 0.02215 -0.0943 0.7361 1.0002 0.500 0.5500 0.03504 0.02178 -0.1002 0.7207 1.0002 0.750 0.5981 0.03599 0.02222 -0.1045 0.7112 1.0002 1.000 0.6308 0.03737 0.02348 -0.1069 0.7086 1.0002 1.250 0.6594 0.03901 0.02506 -0.1090 0.7081 1.0002 1.500 0.6826 0.04101 0.02707 -0.1106 0.7097 1.0002 1.750 0.6988 0.04356 0.02968 -0.1116 0.7132 1.0002 2.000 0.6657 0.04920 0.03559 -0.1076 0.7229 1.0002 2.250 0.6461 0.05459 0.04101 -0.1056 0.7302 1.0002 2.500 0.5939 0.06205 0.04849 -0.1005 0.7423 1.0002 2.750 0.5976 0.06589 0.05224 -0.1007 0.7449 1.0002 3.250 0.5708 0.07463 0.06088 -0.0972 0.7545 1.0002 3.500 0.5710 0.07832 0.06449 -0.0970 0.7585 1.0002 3.750 0.5792 0.08189 0.06798 -0.0977 0.7632 1.0002 4.000 0.5633 0.08572 0.07178 -0.0956 0.7721 1.0002 4.250 0.5621 0.08922 0.07523 -0.0951 0.7788 1.0002 4.500 0.5702 0.09256 0.07850 -0.0957 0.7822 1.0002 4.750 0.5781 0.09575 0.08164 -0.0960 0.7833 1.0002 5.000 0.5836 0.09876 0.08463 -0.0959 0.7826 1.0002