XFOIL Version 6.94 Calculated polar for: GD BAP 02 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1559 0.05406 0.04390 -0.0460 0.9998 0.2755 -2.750 -0.1207 0.05182 0.04139 -0.0487 0.9998 0.2611 -2.500 -0.0844 0.05051 0.03962 -0.0511 0.9998 0.2492 -2.250 -0.0529 0.04898 0.03793 -0.0523 0.9998 0.2422 -2.000 -0.0199 0.04784 0.03648 -0.0537 0.9998 0.2364 -1.750 0.0123 0.04702 0.03536 -0.0547 0.9998 0.2333 -1.500 0.0430 0.04634 0.03446 -0.0553 0.9998 0.2320 -1.250 0.0725 0.04575 0.03372 -0.0556 0.9998 0.2316 -1.000 0.1022 0.04529 0.03311 -0.0557 0.9998 0.2314 -0.750 0.1318 0.04492 0.03264 -0.0558 0.9998 0.2317 -0.500 0.1613 0.04462 0.03233 -0.0559 0.9998 0.2333 -0.250 0.1906 0.04442 0.03224 -0.0560 0.9998 0.2365 0.000 0.2193 0.04442 0.03245 -0.0563 0.9998 0.2416 0.250 0.3799 0.03955 0.02820 -0.0804 0.9102 0.2901 0.500 0.4053 0.03571 0.02505 -0.0779 0.7493 0.3401 0.750 0.5267 0.02933 0.01833 -0.0885 0.6582 1.0002 1.000 0.5994 0.02962 0.01731 -0.0964 0.6094 1.0002 1.250 0.6452 0.03038 0.01740 -0.0997 0.5849 1.0002 1.500 0.6879 0.03119 0.01773 -0.1027 0.5673 1.0002 1.750 0.7291 0.03203 0.01823 -0.1054 0.5535 1.0002 2.000 0.7696 0.03290 0.01889 -0.1082 0.5439 1.0002 2.250 0.8088 0.03380 0.01968 -0.1108 0.5358 1.0002 2.500 0.8508 0.03482 0.02050 -0.1139 0.5285 1.0002 2.750 0.8868 0.03585 0.02154 -0.1159 0.5222 1.0002 3.000 0.9204 0.03692 0.02266 -0.1175 0.5157 1.0002 3.250 0.9549 0.03809 0.02382 -0.1192 0.5100 1.0002 3.500 0.9899 0.03941 0.02514 -0.1210 0.5059 1.0002 3.750 1.0199 0.04084 0.02665 -0.1220 0.5024 1.0002 4.000 1.0447 0.04232 0.02833 -0.1222 0.4988 1.0002 4.250 1.0687 0.04393 0.03011 -0.1222 0.4950 1.0002 4.500 1.0926 0.04568 0.03203 -0.1223 0.4916 1.0002 4.750 1.1158 0.04757 0.03407 -0.1223 0.4891 1.0002 5.000 1.1390 0.04958 0.03619 -0.1223 0.4863 1.0002