XFOIL Version 6.94 Calculated polar for: SD2083 (9.0%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3713 0.00616 0.00208 -0.0773 0.8072 1.0000 0.500 0.4196 0.00616 0.00194 -0.0756 0.7902 1.0000 1.000 0.4686 0.00618 0.00188 -0.0741 0.7712 1.0000 1.500 0.5185 0.00624 0.00186 -0.0727 0.7518 1.0000 2.000 0.5687 0.00633 0.00188 -0.0714 0.7306 1.0000 2.500 0.6190 0.00645 0.00194 -0.0701 0.7061 1.0000 3.000 0.6689 0.00662 0.00203 -0.0687 0.6761 1.0000 3.500 0.7181 0.00686 0.00220 -0.0672 0.6369 1.0000 4.000 0.7657 0.00724 0.00241 -0.0655 0.5843 1.0000 4.500 0.8114 0.00781 0.00277 -0.0635 0.5133 1.0000 5.000 0.8531 0.00872 0.00327 -0.0610 0.4172 1.0000 5.500 0.8912 0.01000 0.00398 -0.0582 0.3003 1.0000 6.000 0.9339 0.01098 0.00471 -0.0562 0.2332 1.0000 6.500 0.9746 0.01214 0.00551 -0.0539 0.1577 1.0000 7.000 1.0126 0.01353 0.00651 -0.0514 0.0843 1.0000 7.500 1.0427 0.01565 0.00816 -0.0475 0.0157 1.0000 8.000 1.0776 0.01729 0.01002 -0.0440 0.0118 1.0000 8.500 1.1100 0.01893 0.01189 -0.0403 0.0110 1.0000 9.000 1.1369 0.02067 0.01381 -0.0359 0.0097 1.0000 9.500 1.1549 0.02279 0.01613 -0.0302 0.0091 1.0000 10.000 1.1715 0.02533 0.01889 -0.0251 0.0086 1.0000 10.500 1.1869 0.02840 0.02224 -0.0204 0.0083 1.0000 11.000 1.2002 0.03225 0.02640 -0.0161 0.0080 1.0000 11.500 1.2084 0.03696 0.03150 -0.0120 0.0079 1.0000 12.000 1.2080 0.04238 0.03740 -0.0081 0.0080 1.0000 12.500 1.1855 0.05100 0.04672 -0.0044 0.0089 1.0000 13.000 1.1454 0.06156 0.05787 -0.0038 0.0096 1.0000 13.500 1.1044 0.07354 0.07028 -0.0072 0.0100 1.0000 14.000 1.0637 0.08782 0.08491 -0.0147 0.0102 1.0000 14.500 1.0245 0.10511 0.10250 -0.0257 0.0102 1.0000 15.000 0.9797 0.12766 0.12529 -0.0401 0.0102 1.0000 15.500 0.9253 0.15732 0.15501 -0.0557 0.0110 1.0000