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 = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.3201 0.07424 0.05738 0.0268 0.9998 0.7326 -2.750 -0.3031 0.07141 0.05456 0.0242 0.9998 0.7383 -2.500 -0.2767 0.06871 0.05193 0.0216 0.9998 0.7508 -2.250 -0.2510 0.06618 0.04944 0.0183 0.9998 0.7663 -2.000 -0.2194 0.06379 0.04709 0.0151 0.9998 0.7912 -1.750 -0.1780 0.06148 0.04498 0.0107 0.9998 0.8337 -1.500 -0.0578 0.05843 0.04220 -0.0114 0.9998 1.0002 -1.250 -0.0549 0.05607 0.03991 -0.0133 0.9998 1.0002 -1.000 -0.0032 0.05486 0.03781 -0.0273 0.9998 1.0002 -0.750 0.0673 0.05543 0.03635 -0.0409 0.9998 1.0002 -0.500 0.1094 0.05616 0.03551 -0.0444 0.9998 1.0002 -0.250 0.1401 0.05680 0.03507 -0.0450 0.9998 1.0002 0.000 0.1665 0.05743 0.03494 -0.0449 0.9998 1.0002 0.250 0.1909 0.05810 0.03506 -0.0447 0.9998 1.0002 0.500 0.2142 0.05883 0.03540 -0.0444 0.9998 1.0002 0.750 0.2363 0.05965 0.03594 -0.0443 0.9998 1.0002 1.000 0.2573 0.06061 0.03672 -0.0442 0.9998 1.0002 1.250 0.2767 0.06175 0.03779 -0.0442 0.9998 1.0002 1.500 0.2936 0.06319 0.03925 -0.0443 0.9998 1.0002 1.750 0.3060 0.06514 0.04131 -0.0445 0.9998 1.0002 2.000 0.3105 0.06800 0.04433 -0.0450 0.9998 1.0002 2.250 0.3069 0.07185 0.04826 -0.0459 0.9998 1.0002 2.500 0.3039 0.07580 0.05218 -0.0470 0.9998 1.0002 2.750 0.3050 0.07937 0.05565 -0.0482 0.9998 1.0002 3.000 0.3091 0.08265 0.05879 -0.0493 0.9998 1.0002 3.250 0.3153 0.08572 0.06172 -0.0504 0.9998 1.0002 3.500 0.3229 0.08867 0.06452 -0.0515 0.9998 1.0002 3.750 0.3315 0.09153 0.06724 -0.0525 0.9998 1.0002 4.000 0.3408 0.09435 0.06991 -0.0535 0.9998 1.0002 4.250 0.3507 0.09713 0.07255 -0.0545 0.9998 1.0002 4.500 0.3609 0.09988 0.07517 -0.0555 0.9998 1.0002 4.750 0.3716 0.10261 0.07779 -0.0565 0.9998 1.0002 5.000 0.3825 0.10534 0.08040 -0.0574 0.9998 1.0002