XFOIL Version 6.94 Calculated polar for: BL BAP 02 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 -0.1752 0.05543 0.04576 -0.0403 0.9998 0.3127 -2.750 -0.1329 0.05371 0.04354 -0.0448 0.9998 0.3032 -2.500 -0.0982 0.05184 0.04152 -0.0471 0.9998 0.2989 -2.250 -0.0624 0.05028 0.03975 -0.0493 0.9998 0.2942 -2.000 -0.0256 0.04904 0.03821 -0.0516 0.9998 0.2896 -1.750 0.0106 0.04809 0.03697 -0.0537 0.9998 0.2864 -1.500 0.0732 0.04682 0.03532 -0.0608 0.9858 0.2854 -1.250 0.1645 0.04448 0.03269 -0.0730 0.9467 0.2926 -1.000 0.2132 0.04237 0.03048 -0.0764 0.8997 0.3020 -0.750 0.2161 0.04175 0.03002 -0.0724 0.8157 0.3061 -0.500 0.2698 0.03985 0.02816 -0.0762 0.7586 0.3235 -0.250 0.3494 0.03659 0.02503 -0.0836 0.7254 0.3733 0.000 0.4127 0.03203 0.02186 -0.0868 0.6974 1.0002 0.250 0.4865 0.03201 0.02007 -0.0934 0.6734 1.0002 0.500 0.5385 0.03248 0.01966 -0.0978 0.6598 1.0002 0.750 0.5845 0.03311 0.01975 -0.1015 0.6509 1.0002 1.000 0.6309 0.03384 0.02001 -0.1054 0.6444 1.0002 1.250 0.6686 0.03468 0.02064 -0.1080 0.6392 1.0002 1.500 0.7052 0.03562 0.02142 -0.1104 0.6339 1.0002 1.750 0.7416 0.03664 0.02230 -0.1127 0.6288 1.0002 2.000 0.7779 0.03776 0.02330 -0.1151 0.6250 1.0002 2.250 0.8114 0.03901 0.02453 -0.1172 0.6238 1.0002 2.500 0.8414 0.04044 0.02603 -0.1189 0.6237 1.0002 2.750 0.8691 0.04209 0.02777 -0.1203 0.6235 1.0002 3.000 0.8945 0.04396 0.02974 -0.1214 0.6230 1.0002 3.250 0.9148 0.04616 0.03207 -0.1220 0.6230 1.0002 3.500 0.9213 0.04920 0.03533 -0.1211 0.6253 1.0002 3.750 0.8932 0.05471 0.04117 -0.1170 0.6333 1.0002 4.000 0.8770 0.06028 0.04686 -0.1151 0.6412 1.0002 4.750 0.6443 0.09185 0.07867 -0.1019 0.7273 1.0002 5.000 0.6045 0.09814 0.08500 -0.0999 0.7682 1.0002