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 = 0.012 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.2552 0.06668 0.05180 -0.0129 0.9998 0.5198 -2.750 -0.2181 0.06428 0.04915 -0.0181 0.9998 0.5190 -2.500 -0.1785 0.06217 0.04674 -0.0235 0.9998 0.5210 -2.250 -0.1434 0.06024 0.04468 -0.0268 0.9998 0.5261 -2.000 -0.1072 0.05859 0.04287 -0.0301 0.9998 0.5344 -1.750 -0.0677 0.05721 0.04123 -0.0342 0.9998 0.5473 -1.500 -0.0348 0.05581 0.03988 -0.0358 0.9998 0.5648 -1.250 -0.0013 0.05455 0.03871 -0.0375 0.9998 0.5901 -1.000 0.0305 0.05331 0.03771 -0.0385 0.9998 0.6296 -0.750 0.0553 0.05173 0.03690 -0.0373 0.9998 0.6917 -0.500 0.0677 0.04894 0.03532 -0.0336 0.9998 0.9602 -0.250 0.1378 0.04978 0.03431 -0.0454 0.9998 1.0002 0.000 0.1760 0.05060 0.03384 -0.0473 0.9998 1.0002 0.250 0.2045 0.05134 0.03374 -0.0472 0.9998 1.0002 0.500 0.2295 0.05211 0.03396 -0.0469 0.9998 1.0002 0.750 0.2525 0.05298 0.03452 -0.0467 0.9998 1.0002 1.000 0.2733 0.05407 0.03546 -0.0466 0.9998 1.0002 1.250 0.2903 0.05558 0.03699 -0.0468 0.9998 1.0002 1.500 0.2958 0.05834 0.03998 -0.0472 0.9998 1.0002 1.750 0.2787 0.06374 0.04565 -0.0486 0.9998 1.0002 2.000 0.2704 0.06838 0.05028 -0.0502 0.9998 1.0002 2.250 0.2714 0.07205 0.05382 -0.0515 0.9998 1.0002 2.500 0.2765 0.07529 0.05690 -0.0527 0.9998 1.0002 2.750 0.2838 0.07831 0.05975 -0.0538 0.9998 1.0002 3.000 0.2926 0.08120 0.06246 -0.0549 0.9998 1.0002 3.250 0.3023 0.08401 0.06509 -0.0559 0.9998 1.0002 3.500 0.3126 0.08676 0.06768 -0.0569 0.9998 1.0002 3.750 0.3235 0.08949 0.07025 -0.0578 0.9998 1.0002 4.000 0.3346 0.09220 0.07280 -0.0588 0.9998 1.0002 4.250 0.3460 0.09490 0.07536 -0.0597 0.9998 1.0002 4.500 0.3577 0.09759 0.07793 -0.0606 0.9998 1.0002 4.750 0.3694 0.10030 0.08051 -0.0616 0.9998 1.0002 5.000 0.3813 0.10301 0.08311 -0.0625 0.9998 1.0002