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 = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1473 0.05262 0.04324 -0.0476 0.9998 0.3024 -2.750 -0.0981 0.05124 0.04123 -0.0538 0.9998 0.2889 -2.500 -0.0632 0.04874 0.03868 -0.0564 0.9998 0.2840 -2.250 -0.0264 0.04688 0.03671 -0.0591 0.9998 0.2796 -2.000 0.0116 0.04548 0.03520 -0.0619 0.9998 0.2782 -1.750 0.0495 0.04447 0.03420 -0.0648 0.9998 0.2798 -1.500 0.1634 0.04128 0.03075 -0.0829 0.9222 0.2876 -1.250 0.1775 0.04010 0.02963 -0.0814 0.7890 0.2895 -1.000 0.3431 0.03433 0.02270 -0.1027 0.7153 0.3157 -0.750 0.4175 0.03346 0.02134 -0.1109 0.6915 0.3542 -0.500 0.4577 0.03235 0.02153 -0.1124 0.6807 0.5132 -0.250 0.4790 0.03050 0.01982 -0.1080 0.6749 1.0002 0.000 0.5255 0.03153 0.01985 -0.1109 0.6690 1.0002 0.250 0.5662 0.03248 0.02033 -0.1138 0.6658 1.0002 0.500 0.6045 0.03345 0.02104 -0.1167 0.6644 1.0002 0.750 0.6408 0.03454 0.02196 -0.1193 0.6624 1.0002 1.000 0.6762 0.03586 0.02316 -0.1217 0.6588 1.0002 1.250 0.7098 0.03739 0.02456 -0.1238 0.6543 1.0002 1.500 0.7396 0.03893 0.02609 -0.1254 0.6512 1.0002 1.750 0.7679 0.04046 0.02767 -0.1271 0.6512 1.0002 2.000 0.7933 0.04215 0.02945 -0.1284 0.6520 1.0002 2.250 0.8158 0.04408 0.03149 -0.1296 0.6530 1.0002 2.500 0.8350 0.04633 0.03384 -0.1305 0.6542 1.0002 2.750 0.8501 0.04894 0.03656 -0.1310 0.6557 1.0002 3.000 0.8440 0.05261 0.04043 -0.1294 0.6587 1.0002 3.250 0.8228 0.05747 0.04544 -0.1266 0.6619 1.0002 3.500 0.7971 0.06287 0.05091 -0.1236 0.6642 1.0002 3.750 0.7704 0.06830 0.05635 -0.1205 0.6650 1.0002 4.000 0.7489 0.07366 0.06170 -0.1183 0.6638 1.0002 4.250 0.7490 0.07767 0.06567 -0.1177 0.6594 1.0002 4.500 0.7616 0.08117 0.06912 -0.1183 0.6560 1.0002 4.750 0.7508 0.08566 0.07359 -0.1172 0.6545 1.0002 5.000 0.7460 0.08969 0.07759 -0.1164 0.6514 1.0002