XFOIL Version 6.94 Calculated polar for: GD BAP 01 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 -0.3131 0.06703 0.05240 0.0273 0.9998 0.6942 -2.500 -0.2546 0.06149 0.04695 0.0195 0.9998 0.7123 -2.000 -0.1902 0.05667 0.04237 0.0133 0.9998 0.7595 -1.500 -0.0455 0.05105 0.03778 -0.0077 0.9998 0.9979 -1.000 0.0500 0.04890 0.03386 -0.0325 0.9998 1.0002 -0.500 0.1285 0.05072 0.03316 -0.0405 0.9998 1.0002 0.000 0.1607 0.05406 0.03565 -0.0418 0.9998 1.0002 0.500 0.1680 0.05948 0.04044 -0.0427 0.9998 1.0002 1.000 0.1811 0.06462 0.04486 -0.0441 0.9998 1.0002 1.500 0.2002 0.06947 0.04901 -0.0458 0.9998 1.0002 2.000 0.2221 0.07418 0.05309 -0.0475 0.9998 1.0002 2.500 0.2456 0.07885 0.05719 -0.0492 0.9998 1.0002 3.000 0.2699 0.08355 0.06139 -0.0509 0.9998 1.0002 3.500 0.2948 0.08832 0.06572 -0.0526 0.9998 1.0002 4.000 0.3199 0.09317 0.07020 -0.0544 0.9998 1.0002 4.500 0.3451 0.09811 0.07481 -0.0562 0.9998 1.0002 5.000 0.3703 0.10313 0.07956 -0.0580 0.9998 1.0002