XFOIL Version 6.94 Calculated polar for: gradus3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.020 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.500 -0.2807 0.04171 0.02954 0.0158 0.9999 0.6419 -2.000 -0.0573 0.03668 0.02389 -0.0203 0.9999 1.0001 -1.500 -0.0069 0.03720 0.02360 -0.0216 0.9999 1.0001 -1.000 0.0441 0.03798 0.02381 -0.0224 0.9999 1.0001 -0.500 0.0942 0.03893 0.02432 -0.0230 0.9999 1.0001 0.000 0.1425 0.04006 0.02530 -0.0232 0.9999 1.0001 0.500 0.1862 0.04164 0.02702 -0.0234 0.9999 1.0001 1.500 0.5373 0.04478 0.03054 -0.0753 0.6869 1.0001 2.000 0.6664 0.04528 0.03040 -0.0860 0.6352 1.0001 2.500 0.6657 0.05145 0.03662 -0.0817 0.6151 1.0001 3.000 0.6631 0.05834 0.04345 -0.0782 0.5979 1.0001 3.500 0.6408 0.06686 0.05194 -0.0742 0.5926 1.0001 4.000 0.6170 0.07593 0.06087 -0.0717 0.5945 1.0001 4.500 0.6062 0.08435 0.06917 -0.0708 0.6010 1.0001 5.000 0.6074 0.09259 0.07730 -0.0711 0.6116 1.0001