XFOIL Version 6.94 Calculated polar for: voyager2 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 ------- -------- --------- --------- -------- ------- ------- -3.000 -0.4220 0.02601 0.01249 0.0108 1.0000 0.1232 -2.750 -0.4058 0.02510 0.01218 0.0132 1.0000 0.2734 -2.500 -0.3915 0.02434 0.01185 0.0158 1.0000 0.3519 -2.250 -0.3835 0.02291 0.01136 0.0196 1.0000 0.4754 -2.000 -0.1108 0.02482 0.01295 -0.0206 1.0000 1.0000 -1.750 -0.0975 0.02471 0.01260 -0.0185 1.0000 1.0000 -1.500 -0.0844 0.02462 0.01232 -0.0164 1.0000 1.0000 -1.250 -0.0716 0.02455 0.01208 -0.0142 1.0000 1.0000 -1.000 -0.0589 0.02450 0.01189 -0.0120 1.0000 1.0000 -0.750 -0.0463 0.02445 0.01174 -0.0097 1.0000 1.0000 -0.500 -0.0339 0.02442 0.01163 -0.0074 1.0000 1.0000 -0.250 -0.0215 0.02440 0.01155 -0.0051 1.0000 1.0000 0.000 -0.0092 0.02439 0.01146 -0.0028 1.0000 1.0000 0.250 0.0031 0.02438 0.01144 -0.0005 1.0000 1.0000 0.500 0.0154 0.02439 0.01146 0.0018 1.0000 1.0000 0.750 0.0278 0.02441 0.01151 0.0042 1.0000 1.0000 1.000 0.0403 0.02444 0.01161 0.0065 1.0000 1.0000 1.250 0.0529 0.02448 0.01176 0.0087 1.0000 1.0000 1.500 0.0657 0.02453 0.01196 0.0110 1.0000 1.0000 1.750 0.0787 0.02461 0.01229 0.0132 1.0000 1.0000 2.000 0.0920 0.02470 0.01260 0.0154 1.0000 1.0000 2.500 0.3665 0.02598 0.01085 -0.0207 0.0860 1.0000 2.750 0.3865 0.02660 0.01170 -0.0191 0.0804 1.0000 3.000 0.4072 0.02714 0.01245 -0.0176 0.0783 1.0000 3.250 0.4278 0.02776 0.01329 -0.0160 0.0776 1.0000 3.500 0.4485 0.02847 0.01421 -0.0144 0.0779 1.0000 3.750 0.4688 0.02929 0.01523 -0.0128 0.0786 1.0000 4.000 0.4887 0.03024 0.01634 -0.0111 0.0798 1.0000 4.250 0.5098 0.03127 0.01756 -0.0095 0.0813 1.0000 4.500 0.5337 0.03194 0.01849 -0.0080 0.0841 1.0000 4.750 0.5642 0.03298 0.01978 -0.0074 0.0882 1.0000 5.000 0.6028 0.03458 0.02156 -0.0080 0.0931 1.0000