XFOIL Version 6.94 Calculated polar for: gradus32 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.040 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.500 -0.2441 0.03350 0.02395 0.0020 0.9999 0.3677 -2.000 -0.1953 0.03466 0.02511 0.0062 0.9798 0.5532 -0.500 0.3967 0.02308 0.01330 -0.0651 0.7088 1.0001 0.000 0.4622 0.02381 0.01303 -0.0650 0.5790 1.0001 0.500 0.5181 0.02516 0.01370 -0.0647 0.4967 1.0001 1.000 0.5726 0.02643 0.01433 -0.0641 0.4491 1.0001 1.500 0.6334 0.02815 0.01576 -0.0653 0.4308 1.0001 2.000 0.6940 0.03014 0.01784 -0.0669 0.4193 1.0001 2.500 0.7496 0.03265 0.02058 -0.0679 0.4113 1.0001 3.000 0.7983 0.03587 0.02404 -0.0682 0.4062 1.0001 3.500 0.8380 0.04007 0.02854 -0.0678 0.4039 1.0001 4.000 0.8679 0.04474 0.03347 -0.0662 0.3983 1.0001 4.500 0.8915 0.04947 0.03844 -0.0637 0.3887 1.0001 5.000 0.8963 0.05624 0.04542 -0.0606 0.3843 1.0001