XFOIL Version 6.94 Calculated polar for: nacd632 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.005 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2683 0.05991 0.03095 -0.0110 0.9994 1.0006 0.250 0.2853 0.06079 0.03159 -0.0104 0.9994 1.0006 0.500 0.3022 0.06176 0.03240 -0.0099 0.9994 1.0006 0.750 0.3188 0.06282 0.03334 -0.0096 0.9994 1.0006 1.000 0.3351 0.06397 0.03442 -0.0093 0.9994 1.0006 1.250 0.3510 0.06522 0.03564 -0.0092 0.9994 1.0006 1.500 0.3664 0.06659 0.03697 -0.0091 0.9994 1.0006 1.750 0.3811 0.06809 0.03852 -0.0092 0.9994 1.0006 2.000 0.3950 0.06973 0.04025 -0.0094 0.9994 1.0006 2.250 0.4080 0.07155 0.04218 -0.0098 0.9994 1.0006 2.500 0.4200 0.07357 0.04434 -0.0103 0.9994 1.0006 2.750 0.4308 0.07582 0.04674 -0.0110 0.9994 1.0006 3.000 0.4402 0.07831 0.04940 -0.0119 0.9994 1.0006 3.250 0.4483 0.08104 0.05228 -0.0130 0.9994 1.0006 3.500 0.4552 0.08401 0.05538 -0.0144 0.9994 1.0006 3.750 0.4614 0.08716 0.05864 -0.0159 0.9994 1.0006 4.000 0.4671 0.09042 0.06201 -0.0175 0.9994 1.0006 4.250 0.4729 0.09375 0.06542 -0.0192 0.9994 1.0006 4.500 0.4789 0.09713 0.06888 -0.0209 0.9994 1.0006 4.750 0.4853 0.10052 0.07234 -0.0227 0.9994 1.0006 5.000 0.4919 0.10391 0.07580 -0.0245 0.9994 1.0006