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 = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1759 0.05618 0.04465 -0.0366 0.9998 0.3455 -2.750 -0.1338 0.05422 0.04216 -0.0417 0.9998 0.3347 -2.500 -0.0971 0.05270 0.04022 -0.0445 0.9998 0.3290 -2.250 -0.0626 0.05124 0.03849 -0.0465 0.9998 0.3255 -2.000 -0.0279 0.05004 0.03700 -0.0483 0.9998 0.3234 -1.750 0.0060 0.04907 0.03573 -0.0498 0.9998 0.3242 -1.500 0.0393 0.04829 0.03468 -0.0510 0.9998 0.3273 -1.250 0.0718 0.04768 0.03381 -0.0519 0.9998 0.3317 -1.000 0.1022 0.04691 0.03311 -0.0524 0.9998 0.3387 -0.750 0.1327 0.04640 0.03263 -0.0528 0.9998 0.3478 -0.500 0.1631 0.04605 0.03235 -0.0533 0.9998 0.3605 -0.250 0.1922 0.04569 0.03234 -0.0538 0.9998 0.3824 0.000 0.2203 0.04549 0.03284 -0.0546 0.9998 0.4173 0.250 0.2334 0.04713 0.03561 -0.0561 0.9998 0.4637 0.500 0.3565 0.04459 0.03328 -0.0764 0.8616 1.0002 0.750 0.4069 0.04423 0.03210 -0.0804 0.8047 1.0002 1.000 0.4709 0.04304 0.03025 -0.0854 0.7688 1.0002 1.250 0.5436 0.04116 0.02782 -0.0912 0.7418 1.0002 1.500 0.6223 0.04005 0.02614 -0.0991 0.7198 1.0002 1.750 0.6783 0.04042 0.02609 -0.1042 0.7029 1.0002 2.000 0.7322 0.04103 0.02631 -0.1090 0.6883 1.0002 2.250 0.7613 0.04272 0.02788 -0.1104 0.6763 1.0002 2.500 0.8022 0.04399 0.02892 -0.1133 0.6652 1.0002 2.750 0.8176 0.04641 0.03140 -0.1130 0.6575 1.0002 3.000 0.8372 0.04883 0.03386 -0.1134 0.6519 1.0002 3.250 0.8574 0.05141 0.03645 -0.1141 0.6479 1.0002 3.500 0.8797 0.05406 0.03909 -0.1151 0.6439 1.0002 3.750 0.8705 0.05857 0.04374 -0.1129 0.6427 1.0002 4.000 0.8514 0.06397 0.04924 -0.1102 0.6431 1.0002 4.500 0.7304 0.08156 0.06697 -0.1013 0.6629 1.0002 4.750 0.7359 0.08605 0.07144 -0.1024 0.6682 1.0002 5.000 0.6939 0.09301 0.07841 -0.1004 0.6868 1.0002