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 = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1616 0.05016 0.04073 -0.0356 0.9998 0.2860 -2.750 -0.1186 0.04849 0.03853 -0.0400 0.9998 0.2748 -2.500 -0.0827 0.04728 0.03711 -0.0419 0.9998 0.2698 -2.250 -0.0478 0.04540 0.03520 -0.0440 0.9998 0.2661 -2.000 -0.0114 0.04394 0.03373 -0.0463 0.9998 0.2623 -1.750 0.1106 0.03959 0.02904 -0.0653 0.9073 0.2585 -1.250 0.3369 0.03408 0.02077 -0.0941 0.6695 0.2759 -1.000 0.3943 0.03418 0.02051 -0.0997 0.6529 0.3014 -0.750 0.4458 0.03442 0.02082 -0.1044 0.6411 0.3454 -0.500 0.4810 0.03246 0.02093 -0.1046 0.6335 1.0002 -0.250 0.5235 0.03372 0.02128 -0.1064 0.6286 1.0002 0.000 0.5610 0.03483 0.02193 -0.1083 0.6264 1.0002 0.250 0.5942 0.03575 0.02267 -0.1099 0.6248 1.0002 0.500 0.6267 0.03677 0.02360 -0.1114 0.6233 1.0002 0.750 0.6580 0.03788 0.02465 -0.1129 0.6222 1.0002 1.000 0.6882 0.03910 0.02585 -0.1142 0.6209 1.0002 1.250 0.7173 0.04065 0.02739 -0.1154 0.6184 1.0002 1.500 0.7438 0.04244 0.02919 -0.1162 0.6148 1.0002 1.750 0.7675 0.04424 0.03106 -0.1166 0.6106 1.0002 2.000 0.7924 0.04652 0.03336 -0.1172 0.6067 1.0002 2.250 0.8143 0.04834 0.03527 -0.1176 0.6050 1.0002 2.500 0.8339 0.05028 0.03732 -0.1177 0.6034 1.0002 2.750 0.8515 0.05249 0.03963 -0.1176 0.6016 1.0002 3.000 0.8676 0.05519 0.04240 -0.1173 0.5983 1.0002 3.250 0.8760 0.05827 0.04559 -0.1160 0.5929 1.0002 3.500 0.8832 0.06193 0.04929 -0.1145 0.5850 1.0002 3.750 0.8835 0.06601 0.05344 -0.1120 0.5739 1.0002 4.000 0.8841 0.07097 0.05839 -0.1093 0.5575 1.0002 4.250 0.8805 0.07516 0.06264 -0.1069 0.5490 1.0002 4.500 0.8811 0.07914 0.06671 -0.1053 0.5442 1.0002 4.750 0.8703 0.08312 0.07076 -0.1029 0.5406 1.0002 5.000 0.8576 0.08732 0.07501 -0.1006 0.5378 1.0002