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 = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.4432 0.02545 0.01263 0.0147 1.0000 0.0867 -2.750 -0.4192 0.02467 0.01170 0.0158 1.0000 0.0925 -2.250 -0.3795 0.02302 0.01071 0.0193 1.0000 0.2782 -2.000 -0.3637 0.02232 0.01044 0.0215 1.0000 0.3538 -1.750 -0.3567 0.02064 0.00997 0.0253 1.0000 0.5095 -1.500 -0.0820 0.02300 0.01213 -0.0168 1.0000 1.0000 -1.250 -0.0694 0.02294 0.01192 -0.0146 1.0000 1.0000 -1.000 -0.0571 0.02289 0.01174 -0.0123 1.0000 1.0000 -0.750 -0.0449 0.02286 0.01161 -0.0100 1.0000 1.0000 -0.500 -0.0329 0.02283 0.01150 -0.0076 1.0000 1.0000 -0.250 -0.0210 0.02281 0.01143 -0.0052 1.0000 1.0000 0.000 -0.0092 0.02280 0.01135 -0.0028 1.0000 1.0000 0.250 0.0026 0.02279 0.01133 -0.0004 1.0000 1.0000 0.500 0.0144 0.02280 0.01134 0.0020 1.0000 1.0000 0.750 0.0263 0.02281 0.01139 0.0044 1.0000 1.0000 1.000 0.0383 0.02283 0.01147 0.0068 1.0000 1.0000 1.250 0.0506 0.02286 0.01162 0.0092 1.0000 1.0000 1.500 0.0630 0.02291 0.01182 0.0115 1.0000 1.0000 1.750 0.0758 0.02297 0.01207 0.0138 1.0000 1.0000 2.000 0.3426 0.02396 0.00964 -0.0268 0.0691 1.0000 2.250 0.3638 0.02441 0.01020 -0.0254 0.0658 1.0000 2.500 0.3865 0.02485 0.01084 -0.0243 0.0650 1.0000 2.750 0.4094 0.02533 0.01170 -0.0232 0.0645 1.0000 3.000 0.4324 0.02593 0.01252 -0.0221 0.0649 1.0000 3.250 0.4547 0.02667 0.01347 -0.0209 0.0658 1.0000 3.500 0.4761 0.02723 0.01425 -0.0194 0.0675 1.0000 3.750 0.4976 0.02782 0.01506 -0.0178 0.0700 1.0000 4.000 0.5200 0.02862 0.01604 -0.0162 0.0731 1.0000 4.250 0.5455 0.02967 0.01720 -0.0151 0.0767 1.0000 4.500 0.5771 0.03146 0.01890 -0.0150 0.0805 1.0000 4.750 0.6034 0.03189 0.01969 -0.0134 0.0860 1.0000 5.000 0.6352 0.03359 0.02156 -0.0129 0.0928 1.0000