XFOIL Version 6.94 Calculated polar for: fauvel bl2 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 -0.1032 0.04280 0.03270 -0.0226 0.9995 0.4698 -2.750 -0.0791 0.04203 0.03190 -0.0231 0.9995 0.4894 -2.500 -0.0543 0.04143 0.03132 -0.0237 0.9995 0.5148 -2.250 -0.0288 0.04092 0.03093 -0.0244 0.9995 0.5467 -2.000 -0.0048 0.04037 0.03078 -0.0243 0.9995 0.5954 -1.750 0.0148 0.03946 0.03078 -0.0228 0.9995 0.6877 -1.500 0.0438 0.03868 0.02997 -0.0262 0.9995 1.0005 -1.250 0.3107 0.03894 0.02823 -0.0605 0.7915 1.0005 -1.000 0.3267 0.04179 0.03066 -0.0547 0.7154 1.0005 -0.750 0.3466 0.04418 0.03269 -0.0517 0.6679 1.0005 -0.500 0.3705 0.04642 0.03469 -0.0515 0.6300 1.0005 -0.250 0.3947 0.04823 0.03623 -0.0505 0.6029 1.0005 0.000 0.4210 0.05040 0.03822 -0.0515 0.5813 1.0005 0.250 0.4471 0.05301 0.04071 -0.0539 0.5644 1.0005 0.500 0.4725 0.05523 0.04274 -0.0547 0.5504 1.0005 0.750 0.4969 0.05760 0.04499 -0.0559 0.5372 1.0005 1.000 0.5191 0.06066 0.04795 -0.0582 0.5277 1.0005 1.250 0.5372 0.06456 0.05182 -0.0617 0.5223 1.0005 1.500 0.5540 0.06825 0.05544 -0.0642 0.5183 1.0005 1.750 0.5728 0.07145 0.05854 -0.0654 0.5138 1.0005 2.000 0.5890 0.07499 0.06197 -0.0668 0.5103 1.0005 2.250 0.5956 0.07949 0.06643 -0.0695 0.5099 1.0005 2.750 0.5754 0.09029 0.07722 -0.0756 0.5270 1.0005 3.250 0.5433 0.10064 0.08753 -0.0794 0.5716 1.0005 4.250 0.4014 0.11203 0.09904 -0.0819 0.9032 1.0005 4.750 0.4634 0.12156 0.10835 -0.0888 0.8522 1.0005 5.000 0.4745 0.12396 0.11068 -0.0887 0.8324 1.0005