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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3774 0.00787 0.00321 -0.0803 0.8384 1.0000 0.500 0.4241 0.00783 0.00303 -0.0781 0.8220 1.0000 1.000 0.4717 0.00782 0.00291 -0.0761 0.8039 1.0000 1.500 0.5202 0.00782 0.00284 -0.0742 0.7841 1.0000 2.000 0.5697 0.00785 0.00282 -0.0726 0.7641 1.0000 2.500 0.6197 0.00790 0.00280 -0.0710 0.7428 1.0000 3.000 0.6692 0.00799 0.00288 -0.0694 0.7158 1.0000 3.500 0.7188 0.00813 0.00299 -0.0678 0.6834 1.0000 4.000 0.7674 0.00835 0.00314 -0.0661 0.6416 1.0000 4.500 0.8142 0.00874 0.00340 -0.0640 0.5844 1.0000 5.000 0.8578 0.00939 0.00379 -0.0615 0.5054 1.0000 5.500 0.8968 0.01045 0.00442 -0.0586 0.4058 1.0000 6.000 0.9319 0.01187 0.00531 -0.0553 0.2920 1.0000 6.500 0.9723 0.01297 0.00619 -0.0530 0.2271 1.0000 7.000 1.0097 0.01432 0.00719 -0.0503 0.1515 1.0000 7.500 1.0416 0.01619 0.00853 -0.0470 0.0654 1.0000 8.000 1.0651 0.01889 0.01104 -0.0419 0.0182 1.0000 8.500 1.0942 0.02078 0.01319 -0.0377 0.0159 1.0000 9.000 1.1137 0.02301 0.01564 -0.0321 0.0147 1.0000 9.500 1.1315 0.02549 0.01828 -0.0270 0.0134 1.0000 10.000 1.1445 0.02984 0.02288 -0.0220 0.0120 1.0000 10.500 1.1678 0.03370 0.02708 -0.0185 0.0118 1.0000 11.000 1.1836 0.03836 0.03224 -0.0146 0.0116 1.0000 11.500 1.1845 0.04395 0.03835 -0.0103 0.0116 1.0000 12.000 1.1704 0.05068 0.04560 -0.0064 0.0116 1.0000 13.500 0.9490 0.07368 0.07012 -0.0072 0.0122 1.0000 14.000 0.9123 0.08469 0.08147 -0.0136 0.0124 1.0000 14.500 0.8733 0.09823 0.09537 -0.0229 0.0127 1.0000 15.500 0.7279 0.15275 0.15035 -0.0566 0.0170 1.0000