XFOIL Version 6.94 Calculated polar for: BL BAP 06 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 -0.1099 0.04803 0.03890 -0.0469 0.9998 0.2383 -2.500 -0.0730 0.04655 0.03698 -0.0490 0.9998 0.2221 -2.250 -0.0369 0.04511 0.03510 -0.0507 0.9998 0.2095 -2.000 -0.0048 0.04427 0.03401 -0.0515 0.9998 0.2030 -1.750 0.0261 0.04311 0.03278 -0.0522 0.9998 0.1989 -1.500 0.0570 0.04225 0.03180 -0.0527 0.9998 0.1951 -1.250 0.0881 0.04160 0.03105 -0.0532 0.9998 0.1927 -1.000 0.1987 0.03948 0.02875 -0.0691 0.9641 0.1955 -0.750 0.2516 0.03541 0.02475 -0.0716 0.8541 0.1984 -0.500 0.5314 0.03371 0.01988 -0.1176 0.5567 0.2375 -0.250 0.5545 0.03331 0.01998 -0.1165 0.5405 0.2694 0.000 0.5603 0.02983 0.01912 -0.1110 0.5270 1.0002 0.250 0.5922 0.03016 0.01876 -0.1105 0.5149 1.0002 0.500 0.6251 0.03064 0.01873 -0.1110 0.5054 1.0002 0.750 0.6564 0.03110 0.01894 -0.1115 0.4967 1.0002 1.000 0.6879 0.03162 0.01924 -0.1122 0.4896 1.0002 1.250 0.7192 0.03211 0.01951 -0.1128 0.4844 1.0002 1.500 0.7507 0.03280 0.02009 -0.1136 0.4795 1.0002 1.750 0.7813 0.03358 0.02082 -0.1143 0.4744 1.0002 2.000 0.8108 0.03429 0.02145 -0.1147 0.4695 1.0002 2.250 0.8397 0.03493 0.02197 -0.1150 0.4651 1.0002 2.500 0.8685 0.03570 0.02264 -0.1152 0.4613 1.0002 2.750 0.8966 0.03699 0.02404 -0.1157 0.4578 1.0002 3.000 0.9241 0.03832 0.02545 -0.1162 0.4549 1.0002 3.250 0.9508 0.03963 0.02684 -0.1164 0.4517 1.0002 3.500 0.9767 0.04090 0.02817 -0.1164 0.4484 1.0002 3.750 1.0023 0.04214 0.02944 -0.1163 0.4452 1.0002 4.000 1.0276 0.04351 0.03083 -0.1162 0.4427 1.0002 4.250 1.0523 0.04510 0.03247 -0.1161 0.4407 1.0002 4.500 1.0718 0.04731 0.03492 -0.1155 0.4389 1.0002 4.750 1.0887 0.04970 0.03757 -0.1147 0.4370 1.0002 5.000 1.1038 0.05223 0.04035 -0.1138 0.4353 1.0002