XFOIL Version 6.94 Calculated polar for: BL BAP 05 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 -0.0545 0.04870 0.03928 -0.0644 0.9524 0.2518 -2.750 -0.0043 0.04571 0.03615 -0.0692 0.9359 0.2438 -2.500 0.0437 0.04322 0.03337 -0.0731 0.9145 0.2379 -2.250 0.0694 0.04153 0.03151 -0.0724 0.8857 0.2353 -2.000 0.0588 0.04108 0.03119 -0.0652 0.8304 0.2342 -1.750 0.2084 0.03588 0.02409 -0.0851 0.6412 0.2333 -1.500 0.2926 0.03521 0.02187 -0.0951 0.6192 0.2362 -1.250 0.3642 0.03505 0.02091 -0.1032 0.6082 0.2439 -1.000 0.4222 0.03493 0.02049 -0.1089 0.6022 0.2583 -0.500 0.5034 0.03390 0.02005 -0.1139 0.5987 0.3188 -0.250 0.5338 0.03135 0.01952 -0.1129 0.5984 1.0002 0.000 0.5749 0.03195 0.01939 -0.1146 0.5979 1.0002 0.250 0.6131 0.03260 0.01968 -0.1166 0.5973 1.0002 0.500 0.6495 0.03330 0.02020 -0.1186 0.5969 1.0002 0.750 0.6847 0.03397 0.02077 -0.1204 0.5974 1.0002 1.000 0.7196 0.03457 0.02130 -0.1223 0.5999 1.0002 1.250 0.7553 0.03524 0.02192 -0.1244 0.6029 1.0002 1.500 0.7844 0.03542 0.02228 -0.1253 0.6071 1.0002 1.750 0.8152 0.03599 0.02298 -0.1267 0.6111 1.0002 2.000 0.8471 0.03685 0.02392 -0.1284 0.6147 1.0002 2.250 0.8722 0.03762 0.02499 -0.1293 0.6208 1.0002 2.500 0.8926 0.03878 0.02654 -0.1301 0.6311 1.0002 2.750 0.9137 0.04064 0.02868 -0.1313 0.6416 1.0002 3.000 0.9051 0.04413 0.03262 -0.1295 0.6581 1.0002 3.500 0.5847 0.07699 0.06619 -0.1043 0.7682 1.0002 4.000 0.5681 0.08521 0.07433 -0.1021 0.7875 1.0002 4.250 0.5787 0.08859 0.07765 -0.1028 0.7897 1.0002 4.750 0.5888 0.09485 0.08381 -0.1023 0.7894 1.0002 5.000 0.5877 0.09733 0.08625 -0.1007 0.7834 1.0002