XFOIL Version 6.96 Calculated polar for: GOE 482 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 0.1909 0.09732 0.09242 -0.1282 0.7785 0.0433 -10.750 0.1969 0.09474 0.08981 -0.1292 0.7730 0.0440 -10.500 0.1977 0.09182 0.08686 -0.1308 0.7684 0.0469 -10.250 0.2127 0.09054 0.08559 -0.1308 0.7626 0.0485 -10.000 0.2203 0.08849 0.08353 -0.1315 0.7566 0.0506 -9.750 0.2261 0.08592 0.08092 -0.1323 0.7515 0.0503 -9.500 0.2265 0.08317 0.07816 -0.1337 0.7456 0.0519 -9.250 0.2423 0.08229 0.07728 -0.1334 0.7388 0.0561 -9.000 0.2490 0.08022 0.07516 -0.1340 0.7331 0.0578 -8.750 0.2533 0.07763 0.07259 -0.1347 0.7267 0.0567 -8.500 0.2570 0.07509 0.07004 -0.1355 0.7204 0.0563 -8.250 0.2627 0.07294 0.06784 -0.1361 0.7147 0.0571 -8.000 0.2661 0.07054 0.06547 -0.1367 0.7076 0.0572 -7.750 0.2682 0.06795 0.06286 -0.1373 0.7009 0.0566 -7.500 0.2680 0.06520 0.06009 -0.1379 0.6940 0.0558 -7.250 0.2702 0.06305 0.05795 -0.1380 0.6864 0.0564 -7.000 0.2687 0.06087 0.05574 -0.1380 0.6797 0.0567 -6.750 0.2693 0.05835 0.05324 -0.1390 0.6720 0.0569 -6.500 0.2714 0.05505 0.04989 -0.1416 0.6654 0.0565 -6.250 0.2756 0.05107 0.04589 -0.1458 0.6582 0.0564 -6.000 0.2855 0.03012 0.02410 -0.1791 0.6528 0.0573 -5.750 0.3143 0.02655 0.01997 -0.1840 0.6460 0.0578 -5.500 0.3427 0.02453 0.01757 -0.1863 0.6377 0.0584 -5.000 0.3996 0.02206 0.01440 -0.1888 0.6225 0.0599 -4.750 0.4281 0.02127 0.01327 -0.1895 0.6153 0.0606 -4.500 0.4560 0.02051 0.01229 -0.1900 0.6081 0.0611 -4.250 0.4834 0.01976 0.01140 -0.1903 0.6008 0.0617 -4.000 0.5108 0.01923 0.01073 -0.1905 0.5944 0.0623 -3.750 0.5382 0.01879 0.01020 -0.1907 0.5876 0.0629 -3.500 0.5657 0.01843 0.00971 -0.1907 0.5814 0.0636 -3.250 0.5931 0.01811 0.00929 -0.1908 0.5754 0.0644 -3.000 0.6205 0.01783 0.00892 -0.1908 0.5692 0.0654 -2.750 0.6479 0.01763 0.00859 -0.1908 0.5638 0.0668 -2.500 0.6753 0.01743 0.00830 -0.1908 0.5585 0.0681 -2.250 0.7025 0.01725 0.00804 -0.1908 0.5528 0.0691 -2.000 0.7297 0.01712 0.00780 -0.1907 0.5477 0.0700 -1.750 0.7571 0.01691 0.00754 -0.1908 0.5432 0.0711 -1.500 0.7842 0.01675 0.00740 -0.1908 0.5380 0.0725 -1.250 0.8113 0.01667 0.00729 -0.1907 0.5331 0.0741 -1.000 0.8384 0.01665 0.00720 -0.1907 0.5288 0.0763 -0.750 0.8656 0.01665 0.00715 -0.1907 0.5247 0.0789 -0.500 0.8925 0.01663 0.00712 -0.1906 0.5202 0.0814 -0.250 0.9195 0.01661 0.00709 -0.1906 0.5158 0.0848 0.000 0.9463 0.01665 0.00708 -0.1905 0.5117 0.0889 0.250 0.9733 0.01671 0.00709 -0.1904 0.5079 0.0950 0.500 0.9997 0.01671 0.00720 -0.1903 0.5037 0.1105 0.750 1.0261 0.01672 0.00732 -0.1903 0.4996 0.1506 1.000 1.0525 0.01674 0.00742 -0.1902 0.4958 0.1935 1.250 1.0791 0.01678 0.00758 -0.1903 0.4922 0.2580 1.500 1.1044 0.01687 0.00785 -0.1900 0.4882 0.3349 1.750 1.1289 0.01702 0.00807 -0.1895 0.4839 0.3729 2.000 1.1535 0.01718 0.00825 -0.1891 0.4799 0.4004 2.250 1.1784 0.01735 0.00842 -0.1887 0.4764 0.4254 2.500 1.2034 0.01750 0.00862 -0.1883 0.4731 0.4557 2.750 1.2267 0.01763 0.00891 -0.1877 0.4692 0.4919 3.000 1.2497 0.01777 0.00919 -0.1870 0.4651 0.5391 3.250 1.2730 0.01793 0.00942 -0.1864 0.4611 0.5924 3.500 1.2963 0.01806 0.00963 -0.1857 0.4576 0.6530 3.750 1.3148 0.01796 0.00988 -0.1839 0.4539 0.8084 4.000 1.3353 0.01808 0.01007 -0.1827 0.4498 1.0000 4.250 1.3571 0.01838 0.01033 -0.1819 0.4460 1.0000 4.500 1.3782 0.01868 0.01056 -0.1809 0.4426 1.0000 4.750 1.3996 0.01901 0.01080 -0.1800 0.4394 1.0000 5.000 1.4177 0.01935 0.01118 -0.1786 0.4354 1.0000 5.250 1.4358 0.01970 0.01154 -0.1772 0.4314 1.0000 5.500 1.4541 0.02008 0.01187 -0.1759 0.4275 1.0000 5.750 1.4731 0.02046 0.01220 -0.1747 0.4240 1.0000 6.000 1.4904 0.02089 0.01264 -0.1733 0.4203 1.0000 6.250 1.5071 0.02135 0.01314 -0.1718 0.4164 1.0000 6.500 1.5239 0.02182 0.01361 -0.1705 0.4127 1.0000 6.750 1.5412 0.02230 0.01407 -0.1692 0.4094 1.0000 7.000 1.5595 0.02279 0.01451 -0.1681 0.4064 1.0000 7.250 1.5742 0.02339 0.01518 -0.1666 0.4027 1.0000 7.500 1.5890 0.02400 0.01584 -0.1651 0.3989 1.0000 7.750 1.6040 0.02463 0.01647 -0.1637 0.3953 1.0000 8.000 1.6198 0.02524 0.01706 -0.1624 0.3919 1.0000 8.250 1.6348 0.02593 0.01777 -0.1612 0.3886 1.0000 8.500 1.6477 0.02674 0.01866 -0.1597 0.3851 1.0000 8.750 1.6611 0.02753 0.01950 -0.1584 0.3817 1.0000 9.000 1.6753 0.02832 0.02031 -0.1571 0.3786 1.0000 9.250 1.6909 0.02906 0.02103 -0.1561 0.3758 1.0000 9.500 1.7058 0.02987 0.02188 -0.1550 0.3730 1.0000 9.750 1.7158 0.03096 0.02307 -0.1535 0.3697 1.0000 10.000 1.7262 0.03204 0.02423 -0.1521 0.3661 1.0000 10.250 1.7376 0.03308 0.02529 -0.1509 0.3626 1.0000 10.500 1.7512 0.03398 0.02618 -0.1498 0.3593 1.0000 10.750 1.7601 0.03524 0.02752 -0.1484 0.3556 1.0000 11.000 1.7639 0.03685 0.02925 -0.1468 0.3510 1.0000 11.250 1.7701 0.03830 0.03072 -0.1453 0.3461 1.0000 11.500 1.7781 0.03964 0.03202 -0.1441 0.3410 1.0000 11.750 1.7767 0.04183 0.03438 -0.1424 0.3354 1.0000 12.000 1.7797 0.04371 0.03629 -0.1410 0.3299 1.0000 12.250 1.7875 0.04522 0.03777 -0.1400 0.3253 1.0000 12.500 1.7861 0.04772 0.04043 -0.1387 0.3203 1.0000 12.750 1.7881 0.04994 0.04273 -0.1376 0.3155 1.0000 13.000 1.7930 0.05187 0.04466 -0.1367 0.3107 1.0000 13.250 1.7916 0.05463 0.04755 -0.1357 0.3057 1.0000 13.500 1.7896 0.05751 0.05053 -0.1349 0.3001 1.0000 13.750 1.7916 0.05995 0.05298 -0.1341 0.2952 1.0000 14.000 1.7892 0.06308 0.05624 -0.1335 0.2903 1.0000 14.250 1.7855 0.06645 0.05973 -0.1330 0.2851 1.0000 14.500 1.7853 0.06936 0.06268 -0.1326 0.2796 1.0000 14.750 1.7786 0.07327 0.06673 -0.1323 0.2740 1.0000 15.000 1.7709 0.07740 0.07095 -0.1322 0.2675 1.0000 15.250 1.7641 0.08144 0.07506 -0.1321 0.2607 1.0000 15.500 1.7533 0.08619 0.07992 -0.1323 0.2532 1.0000 15.750 1.7444 0.09069 0.08448 -0.1325 0.2458 1.0000 16.000 1.7322 0.09579 0.08967 -0.1329 0.2373 1.0000 16.250 1.7219 0.10067 0.09463 -0.1334 0.2290 1.0000 16.500 1.7107 0.10569 0.09967 -0.1341 0.2196 1.0000 16.750 1.6979 0.11105 0.10511 -0.1350 0.2094 1.0000 17.000 1.6848 0.11649 0.11057 -0.1360 0.1981 1.0000 17.250 1.6705 0.12215 0.11622 -0.1372 0.1862 1.0000