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 = 0.070 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.4769 0.02431 0.01300 0.0204 1.0000 0.0678 -2.750 -0.4557 0.02335 0.01191 0.0221 1.0000 0.0670 -2.500 -0.4325 0.02264 0.01102 0.0234 1.0000 0.0672 -2.250 -0.4077 0.02199 0.01019 0.0244 1.0000 0.0695 -2.000 -0.3824 0.02139 0.00946 0.0254 1.0000 0.0770 -1.750 -0.3594 0.02057 0.00917 0.0263 1.0000 0.2430 -1.500 -0.3385 0.02015 0.00901 0.0275 1.0000 0.3068 -1.250 -0.3232 0.01906 0.00878 0.0294 1.0000 0.4336 -1.000 -0.0546 0.02084 0.01161 -0.0127 1.0000 1.0000 -0.750 -0.0430 0.02082 0.01149 -0.0103 1.0000 1.0000 -0.500 -0.0316 0.02080 0.01140 -0.0078 1.0000 1.0000 -0.250 -0.0203 0.02079 0.01134 -0.0053 1.0000 1.0000 0.000 -0.0092 0.02078 0.01126 -0.0028 1.0000 1.0000 0.250 0.0019 0.02077 0.01124 -0.0003 1.0000 1.0000 0.500 0.0130 0.02077 0.01124 0.0023 1.0000 1.0000 0.750 0.0242 0.02077 0.01128 0.0048 1.0000 1.0000 1.000 0.0356 0.02078 0.01136 0.0073 1.0000 1.0000 1.500 0.3284 0.02143 0.00854 -0.0344 0.0501 1.0000 1.750 0.3521 0.02169 0.00897 -0.0335 0.0499 1.0000 2.000 0.3761 0.02202 0.00950 -0.0327 0.0503 1.0000 2.250 0.4001 0.02248 0.01016 -0.0318 0.0511 1.0000 2.500 0.4229 0.02288 0.01088 -0.0307 0.0520 1.0000 2.750 0.4449 0.02324 0.01141 -0.0295 0.0541 1.0000 3.000 0.4661 0.02373 0.01208 -0.0279 0.0569 1.0000 3.250 0.4863 0.02441 0.01290 -0.0262 0.0600 1.0000 3.500 0.5060 0.02535 0.01389 -0.0244 0.0633 1.0000 3.750 0.5285 0.02663 0.01509 -0.0230 0.0665 1.0000 4.000 0.5526 0.02687 0.01555 -0.0213 0.0723 1.0000 4.250 0.5816 0.02842 0.01705 -0.0208 0.0789 1.0000 4.500 0.6087 0.02901 0.01789 -0.0194 0.0866 1.0000 4.750 0.6423 0.03138 0.02025 -0.0194 0.0961 1.0000 5.000 0.6683 0.03192 0.02130 -0.0173 0.1085 1.0000