XFOIL Version 6.94 Calculated polar for: SG6051 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 0.3800 0.00744 0.00308 -0.0839 0.7692 1.0000 0.500 0.4345 0.00745 0.00300 -0.0839 0.7586 1.0000 1.000 0.4901 0.00753 0.00294 -0.0840 0.7474 1.0000 1.500 0.5468 0.00762 0.00300 -0.0845 0.7359 1.0000 2.000 0.6038 0.00767 0.00301 -0.0849 0.7234 1.0000 2.500 0.6606 0.00782 0.00306 -0.0853 0.7081 1.0000 3.000 0.7178 0.00786 0.00313 -0.0857 0.6928 1.0000 3.500 0.7744 0.00803 0.00321 -0.0860 0.6740 1.0000 4.000 0.8311 0.00812 0.00342 -0.0864 0.6532 1.0000 4.500 0.8870 0.00831 0.00360 -0.0866 0.6267 1.0000 5.000 0.9418 0.00858 0.00382 -0.0866 0.5929 1.0000 5.500 0.9926 0.00912 0.00412 -0.0859 0.5269 1.0000 6.000 1.0398 0.01002 0.00468 -0.0848 0.4421 1.0000 6.500 1.0794 0.01153 0.00570 -0.0826 0.3291 1.0000 7.000 1.1151 0.01328 0.00691 -0.0799 0.2222 1.0000 7.500 1.1481 0.01506 0.00823 -0.0768 0.1359 1.0000 8.000 1.1763 0.01696 0.00974 -0.0729 0.0722 1.0000 8.500 1.2016 0.01870 0.01137 -0.0682 0.0479 1.0000 9.000 1.2221 0.02053 0.01332 -0.0629 0.0395 1.0000 9.500 1.2496 0.02212 0.01508 -0.0593 0.0343 1.0000 10.000 1.2600 0.02515 0.01828 -0.0538 0.0286 1.0000 10.500 1.2956 0.02640 0.01964 -0.0521 0.0242 1.0000 11.000 1.3203 0.02850 0.02173 -0.0494 0.0145 1.0000 11.500 1.3130 0.03353 0.02698 -0.0436 0.0092 1.0000 12.000 1.3286 0.03674 0.03040 -0.0407 0.0087 1.0000 12.500 1.3358 0.04080 0.03472 -0.0374 0.0083 1.0000 13.000 1.3396 0.04537 0.03958 -0.0342 0.0080 1.0000 13.500 1.3393 0.05072 0.04529 -0.0314 0.0078 1.0000 14.000 1.3365 0.05664 0.05155 -0.0294 0.0075 1.0000 14.500 1.3290 0.06342 0.05868 -0.0281 0.0073 1.0000 15.000 1.3152 0.07121 0.06682 -0.0278 0.0071 1.0000 15.500 1.2975 0.08033 0.07630 -0.0291 0.0069 1.0000 16.000 1.2749 0.09115 0.08748 -0.0322 0.0068 1.0000 16.500 1.2459 0.10400 0.10069 -0.0375 0.0067 1.0000 17.000 1.2082 0.11971 0.11678 -0.0455 0.0067 1.0000 17.500 1.1614 0.13923 0.13667 -0.0570 0.0069 1.0000 18.000 1.0809 0.17063 0.16846 -0.0762 0.0075 1.0000 20.000 0.9957 0.25907 0.25678 -0.1118 0.0065 1.0000 20.500 0.9999 0.27231 0.27001 -0.1164 0.0057 1.0000 21.000 1.0021 0.28730 0.28499 -0.1207 0.0069 1.0000