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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1549 0.05508 0.04491 -0.0449 0.9998 0.3301 -2.750 -0.1179 0.05246 0.04212 -0.0486 0.9998 0.3252 -2.500 -0.0786 0.05033 0.03979 -0.0525 0.9998 0.3230 -2.250 -0.0394 0.04858 0.03784 -0.0561 0.9998 0.3229 -2.000 -0.0004 0.04712 0.03623 -0.0593 0.9998 0.3239 -1.750 0.0381 0.04596 0.03496 -0.0622 0.9998 0.3251 -1.500 0.0749 0.04517 0.03419 -0.0652 0.9998 0.3264 -1.250 0.1026 0.04545 0.03466 -0.0680 0.9998 0.3282 -1.000 0.2117 0.04237 0.03144 -0.0857 0.8884 0.3407 -0.750 0.2490 0.04146 0.03062 -0.0887 0.8151 0.3545 -0.500 0.3124 0.03940 0.02872 -0.0942 0.7803 0.3926 -0.250 0.3648 0.03592 0.02705 -0.0953 0.7616 0.5873 0.000 0.4233 0.03333 0.02340 -0.0973 0.7448 1.0002 0.250 0.4945 0.03343 0.02212 -0.1040 0.7309 1.0002 0.500 0.5467 0.03420 0.02221 -0.1091 0.7222 1.0002 0.750 0.5949 0.03518 0.02271 -0.1138 0.7168 1.0002 1.000 0.6295 0.03661 0.02395 -0.1167 0.7148 1.0002 1.250 0.6583 0.03835 0.02561 -0.1190 0.7132 1.0002 1.500 0.6823 0.04041 0.02764 -0.1206 0.7114 1.0002 1.750 0.6999 0.04289 0.03012 -0.1215 0.7099 1.0002 2.000 0.7076 0.04609 0.03335 -0.1216 0.7101 1.0002 2.250 0.7072 0.05009 0.03738 -0.1212 0.7133 1.0002 3.000 0.5980 0.06941 0.05683 -0.1125 0.7461 1.0002 3.250 0.5940 0.07359 0.06095 -0.1123 0.7533 1.0002 3.500 0.6034 0.07726 0.06453 -0.1134 0.7582 1.0002 3.750 0.5889 0.08133 0.06858 -0.1119 0.7671 1.0002 4.000 0.5815 0.08507 0.07226 -0.1110 0.7753 1.0002 4.250 0.5876 0.08845 0.07557 -0.1114 0.7792 1.0002 4.500 0.5948 0.09161 0.07867 -0.1117 0.7799 1.0002 4.750 0.6013 0.09458 0.08159 -0.1118 0.7783 1.0002 5.000 0.6087 0.09751 0.08447 -0.1119 0.7758 1.0002