XFOIL Version 6.94 Calculated polar for: fauvel bl3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0997 0.04126 0.03151 -0.0341 0.9995 0.3281 -2.750 -0.0722 0.04075 0.03083 -0.0344 0.9995 0.3432 -2.500 -0.0423 0.04017 0.03020 -0.0352 0.9986 0.3593 -2.250 0.1126 0.03608 0.02614 -0.0558 0.9477 0.4251 -2.000 0.2345 0.02965 0.02187 -0.0644 0.8906 1.0005 -1.750 0.2666 0.02993 0.02146 -0.0606 0.8469 1.0005 -1.500 0.2815 0.03040 0.02162 -0.0540 0.8036 1.0005 -1.250 0.2921 0.03064 0.02161 -0.0465 0.7521 1.0005 -1.000 0.3039 0.03057 0.02125 -0.0393 0.6962 1.0005 -0.750 0.3225 0.03000 0.02046 -0.0346 0.6288 1.0005 -0.500 0.3484 0.02933 0.01953 -0.0323 0.5551 1.0005 -0.250 0.3738 0.02903 0.01875 -0.0299 0.5050 1.0005 0.000 0.3993 0.02903 0.01812 -0.0279 0.4715 1.0005 0.250 0.4260 0.02940 0.01788 -0.0267 0.4467 1.0005 0.500 0.4536 0.03005 0.01798 -0.0260 0.4288 1.0005 0.750 0.4821 0.03090 0.01841 -0.0257 0.4165 1.0005 1.000 0.5108 0.03187 0.01899 -0.0253 0.4073 1.0005 1.250 0.5410 0.03300 0.01997 -0.0257 0.3990 1.0005 1.500 0.5701 0.03420 0.02092 -0.0256 0.3913 1.0005 1.750 0.6001 0.03556 0.02222 -0.0261 0.3842 1.0005 2.000 0.6298 0.03699 0.02354 -0.0264 0.3777 1.0005 2.250 0.6594 0.03857 0.02499 -0.0267 0.3734 1.0005 2.500 0.6904 0.04031 0.02691 -0.0281 0.3703 1.0005 2.750 0.7207 0.04224 0.02899 -0.0294 0.3676 1.0005 3.000 0.7503 0.04432 0.03119 -0.0307 0.3648 1.0005 3.250 0.7789 0.04646 0.03335 -0.0317 0.3617 1.0005 3.500 0.8067 0.04895 0.03592 -0.0330 0.3590 1.0005 3.750 0.8325 0.05224 0.03957 -0.0357 0.3576 1.0005 4.000 0.8562 0.05600 0.04362 -0.0384 0.3581 1.0005 4.250 0.8775 0.06013 0.04796 -0.0410 0.3595 1.0005 4.500 0.8387 0.07686 0.06566 -0.0551 0.3761 1.0005