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 = 0.045 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.750 0.1680 0.03871 0.02633 -0.0992 0.5959 0.2003 -2.500 0.2508 0.03811 0.02505 -0.1106 0.5801 0.1956 -2.250 0.2984 0.03769 0.02445 -0.1146 0.5705 0.1960 -2.000 0.3461 0.03781 0.02437 -0.1184 0.5629 0.1979 -1.750 0.3869 0.03816 0.02457 -0.1207 0.5593 0.1999 -1.500 0.4213 0.03804 0.02436 -0.1216 0.5577 0.2020 -1.250 0.4544 0.03790 0.02417 -0.1222 0.5572 0.2053 -1.000 0.4859 0.03767 0.02408 -0.1227 0.5575 0.2114 -0.750 0.5171 0.03770 0.02422 -0.1232 0.5578 0.2220 -0.500 0.5483 0.03775 0.02445 -0.1239 0.5581 0.2414 -0.250 0.5800 0.03756 0.02475 -0.1249 0.5589 0.2913 0.000 0.6035 0.03485 0.02381 -0.1223 0.5610 1.0002 0.250 0.6364 0.03442 0.02300 -0.1227 0.5658 1.0002 0.500 0.6694 0.03442 0.02282 -0.1237 0.5720 1.0002 0.750 0.7030 0.03493 0.02318 -0.1252 0.5781 1.0002 1.000 0.7366 0.03553 0.02368 -0.1267 0.5833 1.0002 1.250 0.7680 0.03469 0.02296 -0.1277 0.5901 1.0002 1.500 0.8011 0.03480 0.02311 -0.1292 0.5975 1.0002 1.750 0.8352 0.03478 0.02317 -0.1311 0.6062 1.0002 2.000 0.8659 0.03462 0.02329 -0.1329 0.6182 1.0002 2.250 0.8919 0.03518 0.02426 -0.1345 0.6327 1.0002 2.500 0.9187 0.03667 0.02591 -0.1359 0.6376 1.0002 2.750 0.9434 0.03844 0.02778 -0.1368 0.6390 1.0002 3.000 0.9628 0.04049 0.02996 -0.1370 0.6397 1.0002 3.250 0.9788 0.04277 0.03236 -0.1366 0.6379 1.0002 3.500 0.9915 0.04530 0.03499 -0.1356 0.6343 1.0002 3.750 0.9935 0.04844 0.03828 -0.1332 0.6295 1.0002 4.000 1.0219 0.05078 0.04056 -0.1340 0.6226 1.0002 4.250 1.0300 0.05403 0.04387 -0.1323 0.6163 1.0002 4.500 1.0142 0.05864 0.04859 -0.1278 0.6085 1.0002 4.750 0.9959 0.06383 0.05383 -0.1229 0.5974 1.0002