XFOIL Version 6.94 Calculated polar for: gradus2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.120 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -2.500 -0.1355 0.02177 0.01334 -0.0163 0.9627 0.2012 -2.000 -0.0458 0.02140 0.01384 -0.0210 0.9331 0.4847 -1.500 0.0475 0.01909 0.01149 -0.0248 0.8780 0.5341 -1.000 0.1662 0.01866 0.00846 -0.0343 0.3377 0.5805 -0.500 0.2148 0.01915 0.00855 -0.0326 0.3147 0.6065 0.000 0.2722 0.01938 0.00855 -0.0330 0.2989 0.6250 0.500 0.3439 0.01980 0.00874 -0.0367 0.2870 0.6425 1.000 0.4401 0.02050 0.00920 -0.0463 0.2762 0.6647 1.500 0.5274 0.02090 0.00975 -0.0537 0.2682 0.6898 2.000 0.6968 0.02241 0.01175 -0.0795 0.2564 0.9708 2.500 0.7914 0.02395 0.01335 -0.0883 0.2517 1.0001 3.000 0.8459 0.02506 0.01453 -0.0881 0.2479 1.0001 3.500 0.8989 0.02628 0.01583 -0.0876 0.2436 1.0001 4.000 0.9506 0.02770 0.01730 -0.0869 0.2400 1.0001 4.500 1.0016 0.03002 0.01964 -0.0865 0.2359 1.0001 5.000 1.0458 0.03118 0.02116 -0.0842 0.2308 1.0001