XFOIL Version 6.94 Calculated polar for: FX 63-110 AIRFOIL 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 0.6779 0.00791 0.00265 -0.1557 0.7231 0.6305 0.500 0.7336 0.00800 0.00278 -0.1553 0.7064 0.6588 1.000 0.7890 0.00813 0.00290 -0.1548 0.6876 0.6816 1.500 0.8434 0.00827 0.00297 -0.1542 0.6622 0.6998 2.000 0.8979 0.00845 0.00310 -0.1536 0.6385 0.7178 2.500 0.9519 0.00863 0.00332 -0.1529 0.6151 0.7367 3.000 1.0047 0.00886 0.00353 -0.1521 0.5843 0.7552 3.500 1.0480 0.00958 0.00377 -0.1494 0.4798 0.7756 4.000 1.0891 0.01078 0.00437 -0.1468 0.3636 0.8013 4.500 1.1275 0.01215 0.00520 -0.1439 0.2420 0.8394 5.500 1.1959 0.01518 0.00726 -0.1367 0.0594 1.0000 6.000 1.2404 0.01640 0.00826 -0.1351 0.0290 1.0000 6.500 1.2855 0.01743 0.00922 -0.1335 0.0167 1.0000 7.000 1.3262 0.01875 0.01048 -0.1311 0.0021 1.0000 7.500 1.3685 0.01976 0.01158 -0.1290 0.0020 1.0000 8.000 1.4076 0.02089 0.01282 -0.1263 0.0020 1.0000 8.500 1.4396 0.02214 0.01420 -0.1225 0.0020 1.0000 9.000 1.4675 0.02356 0.01577 -0.1182 0.0020 1.0000 9.500 1.4927 0.02523 0.01760 -0.1139 0.0021 1.0000 10.000 1.5148 0.02721 0.01977 -0.1095 0.0022 1.0000 10.500 1.5336 0.02960 0.02236 -0.1054 0.0023 1.0000 11.000 1.5492 0.03247 0.02545 -0.1015 0.0024 1.0000 11.500 1.5617 0.03591 0.02912 -0.0980 0.0026 1.0000 12.000 1.5687 0.04018 0.03366 -0.0950 0.0026 1.0000 12.500 1.5733 0.04506 0.03878 -0.0927 0.0027 1.0000 13.000 1.5803 0.05005 0.04399 -0.0912 0.0029 1.0000 13.500 1.5834 0.05591 0.05009 -0.0905 0.0031 1.0000 14.000 1.5780 0.06342 0.05788 -0.0908 0.0032 1.0000 14.500 1.5662 0.07258 0.06732 -0.0923 0.0034 1.0000 15.000 1.5503 0.08328 0.07829 -0.0954 0.0035 1.0000 15.500 1.5308 0.09549 0.09079 -0.0999 0.0036 1.0000 16.000 1.5093 0.10876 0.10433 -0.1057 0.0037 1.0000 16.500 1.4899 0.12200 0.11777 -0.1120 0.0038 1.0000 17.000 1.4819 0.13341 0.12943 -0.1180 0.0039 1.0000 17.500 1.4760 0.14469 0.14099 -0.1243 0.0041 1.0000 18.000 1.4691 0.15600 0.15257 -0.1308 0.0044 1.0000 18.500 1.4596 0.16797 0.16477 -0.1383 0.0046 1.0000 19.000 1.4533 0.17893 0.17594 -0.1452 0.0049 1.0000 20.000 1.4442 0.20038 0.19774 -0.1598 0.0052 1.0000 20.500 1.4303 0.21520 0.21285 -0.1706 0.0054 1.0000 21.000 1.4159 0.22998 0.22784 -0.1815 0.0053 1.0000 21.500 1.3919 0.24928 0.24738 -0.1953 0.0052 1.0000