XFOIL Version 6.96 Calculated polar for: FX 73-CL2-152 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.4651 0.05320 0.04993 -0.1085 0.9673 0.0262 -11.250 -0.4963 0.04538 0.04195 -0.1152 0.9553 0.0264 -11.000 -0.5130 0.03854 0.03495 -0.1223 0.9443 0.0265 -10.750 -0.5021 0.03203 0.02823 -0.1332 0.9359 0.0269 -10.500 -0.4717 0.02671 0.02265 -0.1453 0.9277 0.0273 -10.250 -0.4412 0.02398 0.01969 -0.1515 0.9185 0.0277 -9.750 -0.3696 0.02062 0.01600 -0.1598 0.9000 0.0285 -9.500 -0.3214 0.01928 0.01456 -0.1652 0.8871 0.0290 -9.250 -0.2367 0.01781 0.01289 -0.1776 0.8603 0.0298 -9.000 -0.1487 0.01705 0.01158 -0.1907 0.7775 0.0309 -8.750 -0.1224 0.01686 0.01096 -0.1911 0.7094 0.0315 -8.500 -0.0991 0.01658 0.01037 -0.1907 0.6615 0.0319 -8.250 -0.0736 0.01628 0.00980 -0.1907 0.6257 0.0324 -8.000 -0.0460 0.01586 0.00923 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0.4282 0.0668 -2.500 0.6173 0.01213 0.00396 -0.2020 0.4253 0.0752 -2.250 0.6481 0.01205 0.00391 -0.2025 0.4226 0.0903 -2.000 0.6787 0.01199 0.00390 -0.2030 0.4196 0.1149 -1.500 0.7386 0.01196 0.00395 -0.2037 0.4144 0.1586 -1.250 0.7681 0.01196 0.00398 -0.2038 0.4122 0.1738 -1.000 0.7974 0.01199 0.00402 -0.2040 0.4097 0.1868 -0.750 0.8263 0.01203 0.00406 -0.2040 0.4069 0.1984 -0.500 0.8552 0.01208 0.00411 -0.2040 0.4039 0.2108 -0.250 0.8839 0.01215 0.00418 -0.2040 0.4013 0.2238 0.000 0.9125 0.01223 0.00427 -0.2041 0.3987 0.2423 0.250 0.9415 0.01229 0.00436 -0.2041 0.3967 0.2594 0.500 0.9705 0.01233 0.00443 -0.2042 0.3947 0.2726 0.750 0.9992 0.01238 0.00451 -0.2042 0.3924 0.2843 1.000 1.0277 0.01245 0.00460 -0.2042 0.3901 0.2985 1.250 1.0561 0.01252 0.00470 -0.2041 0.3876 0.3152 1.500 1.0843 0.01261 0.00481 -0.2041 0.3852 0.3321 1.750 1.1123 0.01272 0.00493 -0.2040 0.3828 0.3512 2.000 1.1401 0.01285 0.00508 -0.2038 0.3806 0.3721 2.250 1.1682 0.01295 0.00522 -0.2038 0.3788 0.3921 2.500 1.1965 0.01302 0.00536 -0.2037 0.3771 0.4130 2.750 1.2247 0.01311 0.00551 -0.2037 0.3752 0.4364 3.000 1.2525 0.01321 0.00566 -0.2035 0.3731 0.4594 3.250 1.2801 0.01331 0.00582 -0.2034 0.3707 0.4817 3.500 1.3073 0.01343 0.00599 -0.2031 0.3683 0.5071 3.750 1.3340 0.01357 0.00617 -0.2028 0.3658 0.5331 4.000 1.3602 0.01373 0.00636 -0.2024 0.3633 0.5565 4.250 1.3869 0.01388 0.00656 -0.2021 0.3613 0.5809 4.500 1.4139 0.01398 0.00676 -0.2018 0.3594 0.6072 4.750 1.4404 0.01410 0.00695 -0.2014 0.3572 0.6344 5.000 1.4664 0.01423 0.00716 -0.2010 0.3548 0.6608 5.250 1.4919 0.01437 0.00737 -0.2004 0.3524 0.6891 5.500 1.5168 0.01452 0.00759 -0.1998 0.3499 0.7188 6.000 1.5644 0.01487 0.00807 -0.1980 0.3447 0.7906 6.250 1.5861 0.01490 0.00828 -0.1966 0.3424 0.8554 6.500 1.5992 0.01486 0.00836 -0.1935 0.3400 1.0000 6.750 1.6238 0.01507 0.00859 -0.1928 0.3373 1.0000 7.000 1.6478 0.01530 0.00882 -0.1920 0.3345 1.0000 7.250 1.6708 0.01556 0.00907 -0.1911 0.3318 1.0000 7.500 1.6931 0.01585 0.00935 -0.1901 0.3291 1.0000 7.750 1.7167 0.01608 0.00963 -0.1893 0.3266 1.0000 8.000 1.7400 0.01632 0.00990 -0.1885 0.3235 1.0000 8.250 1.7625 0.01658 0.01019 -0.1875 0.3202 1.0000 8.500 1.7842 0.01688 0.01051 -0.1864 0.3170 1.0000 8.750 1.8044 0.01723 0.01085 -0.1851 0.3135 1.0000 9.000 1.8258 0.01752 0.01118 -0.1839 0.3087 1.0000 9.250 1.8451 0.01788 0.01153 -0.1825 0.3016 1.0000 9.500 1.8629 0.01832 0.01195 -0.1808 0.2949 1.0000 9.750 1.8825 0.01870 0.01236 -0.1795 0.2887 1.0000 10.000 1.8993 0.01921 0.01286 -0.1777 0.2830 1.0000 10.250 1.9172 0.01968 0.01336 -0.1761 0.2779 1.0000 10.500 1.9348 0.02018 0.01388 -0.1745 0.2723 1.0000 10.750 1.9496 0.02081 0.01451 -0.1726 0.2672 1.0000 11.000 1.9661 0.02137 0.01511 -0.1709 0.2630 1.0000 11.250 1.9824 0.02195 0.01574 -0.1692 0.2584 1.0000 11.500 1.9960 0.02267 0.01648 -0.1672 0.2536 1.0000 11.750 2.0087 0.02345 0.01729 -0.1651 0.2493 1.0000 12.000 2.0233 0.02415 0.01805 -0.1633 0.2444 1.0000 12.250 2.0346 0.02505 0.01898 -0.1612 0.2390 1.0000 12.500 2.0440 0.02608 0.02003 -0.1589 0.2340 1.0000 12.750 2.0556 0.02700 0.02102 -0.1570 0.2287 1.0000 13.000 2.0628 0.02823 0.02229 -0.1546 0.2228 1.0000 13.250 2.0702 0.02950 0.02360 -0.1524 0.2171 1.0000 13.500 2.0752 0.03099 0.02513 -0.1502 0.2096 1.0000 13.750 2.0766 0.03282 0.02699 -0.1477 0.2016 1.0000 14.000 2.0724 0.03520 0.02939 -0.1451 0.1916 1.0000 14.250 2.0668 0.03790 0.03210 -0.1428 0.1806 1.0000 14.500 2.0558 0.04133 0.03557 -0.1407 0.1698 1.0000 14.750 2.0396 0.04564 0.03990 -0.1390 0.1593 1.0000 15.000 2.0203 0.05074 0.04505 -0.1379 0.1502 1.0000 15.250 1.9998 0.05642 0.05082 -0.1376 0.1419 1.0000 15.500 1.9772 0.06277 0.05726 -0.1378 0.1354 1.0000 15.750 1.9537 0.06954 0.06413 -0.1385 0.1294 1.0000 16.000 1.9284 0.07683 0.07152 -0.1396 0.1244 1.0000 16.250 1.9066 0.08377 0.07857 -0.1409 0.1193 1.0000 16.500 1.8822 0.09127 0.08616 -0.1425 0.1147 1.0000