XFOIL Version 6.94 Calculated polar for: SG6040 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 0.3845 0.01115 0.00513 -0.0891 0.7188 0.7022 0.500 0.4397 0.01111 0.00502 -0.0889 0.7030 0.7097 1.000 0.4934 0.01113 0.00501 -0.0884 0.6862 0.7179 1.500 0.5477 0.01116 0.00498 -0.0882 0.6694 0.7258 2.000 0.6011 0.01123 0.00505 -0.0876 0.6530 0.7333 2.500 0.6554 0.01134 0.00512 -0.0874 0.6364 0.7418 3.000 0.7085 0.01144 0.00523 -0.0869 0.6200 0.7497 3.500 0.7618 0.01161 0.00537 -0.0865 0.6034 0.7586 4.000 0.8139 0.01177 0.00554 -0.0858 0.5859 0.7680 4.500 0.8633 0.01194 0.00574 -0.0846 0.5657 0.7782 5.000 0.9107 0.01209 0.00596 -0.0829 0.5441 0.7895 5.500 0.9572 0.01231 0.00620 -0.0812 0.5212 0.8029 6.000 1.0011 0.01253 0.00650 -0.0789 0.4986 0.8171 6.500 1.0427 0.01282 0.00685 -0.0762 0.4756 0.8346 7.000 1.0793 0.01311 0.00724 -0.0726 0.4490 0.8575 7.500 1.1074 0.01340 0.00764 -0.0672 0.4212 0.8895 8.000 1.1390 0.01372 0.00808 -0.0628 0.3906 1.0000 8.500 1.1707 0.01459 0.00883 -0.0594 0.3529 1.0000 9.000 1.1918 0.01582 0.00986 -0.0543 0.3077 1.0000 9.500 1.2051 0.01751 0.01131 -0.0486 0.2537 1.0000 10.000 1.2109 0.01985 0.01336 -0.0425 0.1989 1.0000 10.500 1.2178 0.02247 0.01578 -0.0374 0.1557 1.0000 11.000 1.2253 0.02536 0.01853 -0.0330 0.1249 1.0000 11.500 1.2302 0.02870 0.02178 -0.0291 0.1026 1.0000 12.000 1.2355 0.03231 0.02536 -0.0259 0.0873 1.0000 12.500 1.2438 0.03597 0.02908 -0.0234 0.0764 1.0000 13.000 1.2531 0.03979 0.03303 -0.0215 0.0684 1.0000 13.500 1.2540 0.04462 0.03789 -0.0197 0.0624 1.0000 14.000 1.2661 0.04870 0.04213 -0.0189 0.0574 1.0000 14.500 1.2671 0.05400 0.04743 -0.0180 0.0528 1.0000 15.000 1.2795 0.05846 0.05212 -0.0178 0.0499 1.0000 15.500 1.2882 0.06346 0.05724 -0.0179 0.0468 1.0000 16.000 1.2969 0.06835 0.06216 -0.0176 0.0439 1.0000 16.500 1.3057 0.07373 0.06780 -0.0184 0.0418 1.0000 17.000 1.3137 0.07931 0.07356 -0.0194 0.0397 1.0000 17.500 1.3221 0.08483 0.07917 -0.0205 0.0379 1.0000 18.000 1.3321 0.09016 0.08467 -0.0210 0.0363 1.0000 18.500 1.3312 0.09752 0.09235 -0.0234 0.0353 1.0000 19.000 1.3277 0.10539 0.10052 -0.0264 0.0342 1.0000 19.500 1.3206 0.11405 0.10948 -0.0302 0.0332 1.0000 20.000 1.3132 0.12291 0.11856 -0.0347 0.0322 1.0000 20.500 1.3068 0.13163 0.12747 -0.0394 0.0314 1.0000 21.000 1.2933 0.14177 0.13784 -0.0451 0.0307 1.0000 21.500 1.2567 0.15702 0.15347 -0.0547 0.0304 1.0000