XFOIL Version 6.94 Calculated polar for: SD7037-092-88 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 0.3792 0.00571 0.00182 -0.0788 0.7833 0.9902 0.500 0.4355 0.00585 0.00170 -0.0787 0.7456 1.0000 1.000 0.4874 0.00608 0.00168 -0.0776 0.7050 1.0000 1.500 0.5396 0.00637 0.00172 -0.0767 0.6639 1.0000 2.000 0.5920 0.00669 0.00183 -0.0758 0.6223 1.0000 2.500 0.6443 0.00704 0.00198 -0.0750 0.5797 1.0000 3.000 0.6965 0.00743 0.00218 -0.0742 0.5375 1.0000 3.500 0.7485 0.00786 0.00243 -0.0734 0.4940 1.0000 4.000 0.8001 0.00832 0.00274 -0.0726 0.4506 1.0000 4.500 0.8511 0.00886 0.00310 -0.0718 0.4058 1.0000 5.000 0.9020 0.00941 0.00353 -0.0709 0.3618 1.0000 5.500 0.9519 0.01006 0.00402 -0.0700 0.3180 1.0000 6.000 1.0012 0.01077 0.00459 -0.0690 0.2736 1.0000 6.500 1.0493 0.01158 0.00523 -0.0679 0.2279 1.0000 7.000 1.0963 0.01248 0.00598 -0.0666 0.1871 1.0000 7.500 1.1428 0.01339 0.00677 -0.0653 0.1490 1.0000 8.000 1.1882 0.01437 0.00768 -0.0639 0.1178 1.0000 8.500 1.2313 0.01550 0.00871 -0.0621 0.0867 1.0000 9.000 1.2707 0.01692 0.00998 -0.0599 0.0545 1.0000 9.500 1.2993 0.01923 0.01205 -0.0562 0.0196 1.0000 10.000 1.3302 0.02105 0.01400 -0.0526 0.0152 1.0000 10.500 1.3508 0.02307 0.01624 -0.0475 0.0137 1.0000 11.000 1.3662 0.02524 0.01865 -0.0422 0.0129 1.0000 11.500 1.3764 0.02791 0.02153 -0.0371 0.0122 1.0000 12.000 1.3811 0.03128 0.02512 -0.0325 0.0117 1.0000 12.500 1.3792 0.03563 0.02969 -0.0288 0.0111 1.0000 13.000 1.3686 0.04156 0.03588 -0.0261 0.0107 1.0000 13.500 1.3608 0.04799 0.04262 -0.0251 0.0105 1.0000 14.000 1.3558 0.05473 0.04965 -0.0254 0.0103 1.0000 14.500 1.3471 0.06251 0.05776 -0.0269 0.0102 1.0000 15.000 1.3335 0.07171 0.06727 -0.0298 0.0102 1.0000 15.500 1.3163 0.08227 0.07817 -0.0341 0.0101 1.0000 16.000 1.2949 0.09439 0.09061 -0.0400 0.0101 1.0000 16.500 1.2689 0.10831 0.10487 -0.0475 0.0101 1.0000 17.000 1.2410 0.12361 0.12048 -0.0565 0.0101 1.0000 17.500 1.2093 0.14090 0.13808 -0.0671 0.0102 1.0000 18.000 1.1739 0.16027 0.15774 -0.0794 0.0104 1.0000 18.500 1.1391 0.18146 0.17917 -0.0928 0.0106 1.0000