GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 200,000 Max Cl/Cd: 72.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe441-il-200000-n5.txt Download as CSV file: xf-goe441-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0428 0.10835 0.10415 -0.0956 0.8619 0.0510
-10.250 0.0472 0.10538 0.10113 -0.0973 0.8523 0.0512
-10.000 0.0445 0.10046 0.09616 -0.1000 0.8431 0.0459
-9.750 0.0605 0.09847 0.09412 -0.0993 0.8325 0.0455
-9.500 0.0717 0.09616 0.09177 -0.0997 0.8217 0.0449
-9.250 0.0798 0.09347 0.08902 -0.1006 0.8125 0.0444
-8.250 0.0959 0.07920 0.07455 -0.1081 0.7765 0.0401
-7.750 0.0225 0.03187 0.02646 -0.1698 0.7661 0.0403
-7.500 0.0585 0.02574 0.01941 -0.1816 0.7583 0.0409
-7.250 0.0867 0.02452 0.01807 -0.1832 0.7493 0.0413
-7.000 0.1159 0.02344 0.01679 -0.1847 0.7398 0.0418
-6.750 0.1450 0.02240 0.01557 -0.1860 0.7296 0.0425
-6.500 0.1747 0.02144 0.01438 -0.1873 0.7191 0.0433
-6.250 0.2041 0.02054 0.01326 -0.1883 0.7074 0.0443
-6.000 0.2338 0.01968 0.01211 -0.1893 0.6956 0.0455
-5.750 0.2626 0.01903 0.01130 -0.1899 0.6812 0.0464
-5.500 0.2909 0.01854 0.01073 -0.1903 0.6635 0.0473
-5.250 0.3190 0.01809 0.01012 -0.1905 0.6414 0.0483
-5.000 0.3466 0.01768 0.00949 -0.1907 0.6130 0.0496
-4.750 0.3735 0.01735 0.00887 -0.1906 0.5862 0.0509
-4.500 0.4003 0.01711 0.00843 -0.1906 0.5674 0.0523
-4.250 0.4274 0.01697 0.00814 -0.1906 0.5541 0.0543
-4.000 0.4552 0.01681 0.00781 -0.1907 0.5436 0.0569
-3.750 0.4830 0.01670 0.00760 -0.1908 0.5352 0.0596
-3.500 0.5114 0.01658 0.00738 -0.1910 0.5278 0.0630
-3.250 0.5396 0.01652 0.00724 -0.1912 0.5213 0.0666
-3.000 0.5681 0.01647 0.00710 -0.1913 0.5161 0.0717
-2.750 0.5967 0.01647 0.00708 -0.1915 0.5112 0.0776
-2.500 0.6251 0.01651 0.00706 -0.1916 0.5066 0.0844
-2.250 0.6534 0.01656 0.00702 -0.1917 0.5021 0.0914
-2.000 0.6815 0.01666 0.00698 -0.1918 0.4981 0.0989
-1.750 0.7103 0.01662 0.00695 -0.1920 0.4940 0.1061
-1.500 0.7390 0.01659 0.00691 -0.1922 0.4898 0.1135
-1.250 0.7674 0.01663 0.00690 -0.1924 0.4861 0.1212
-1.000 0.7959 0.01665 0.00690 -0.1926 0.4827 0.1286
-0.750 0.8243 0.01675 0.00692 -0.1928 0.4795 0.1362
-0.500 0.8529 0.01678 0.00699 -0.1930 0.4763 0.1448
-0.250 0.8812 0.01681 0.00707 -0.1931 0.4728 0.1550
0.000 0.9093 0.01687 0.00716 -0.1932 0.4692 0.1686
0.250 0.9373 0.01695 0.00726 -0.1933 0.4659 0.1859
0.500 0.9654 0.01705 0.00736 -0.1934 0.4630 0.2070
0.750 0.9935 0.01718 0.00747 -0.1935 0.4602 0.2298
1.000 1.0215 0.01728 0.00761 -0.1937 0.4573 0.2552
1.250 1.0492 0.01730 0.00779 -0.1938 0.4541 0.2961
1.500 1.0765 0.01735 0.00804 -0.1938 0.4508 0.3622
1.750 1.1035 0.01749 0.00826 -0.1937 0.4479 0.4132
2.000 1.1303 0.01765 0.00846 -0.1936 0.4450 0.4497
2.250 1.1569 0.01785 0.00866 -0.1934 0.4422 0.4792
2.500 1.1838 0.01809 0.00887 -0.1933 0.4395 0.5072
2.750 1.2098 0.01823 0.00911 -0.1930 0.4366 0.5327
3.000 1.2357 0.01838 0.00936 -0.1927 0.4337 0.5598
3.250 1.2613 0.01853 0.00960 -0.1924 0.4306 0.5902
3.750 1.3107 0.01881 0.01007 -0.1913 0.4248 0.6866
4.250 1.3526 0.01886 0.01039 -0.1884 0.4196 1.0000
4.500 1.3771 0.01912 0.01068 -0.1880 0.4164 1.0000
4.750 1.4013 0.01940 0.01095 -0.1875 0.4131 1.0000
5.000 1.4252 0.01969 0.01122 -0.1869 0.4100 1.0000
5.250 1.4489 0.01998 0.01148 -0.1863 0.4071 1.0000
5.500 1.4726 0.02031 0.01174 -0.1858 0.4044 1.0000
5.750 1.4959 0.02064 0.01207 -0.1851 0.4016 1.0000
6.000 1.5178 0.02097 0.01245 -0.1843 0.3983 1.0000
6.250 1.5393 0.02131 0.01282 -0.1833 0.3951 1.0000
6.500 1.5603 0.02165 0.01317 -0.1823 0.3921 1.0000
6.750 1.5805 0.02200 0.01351 -0.1812 0.3895 1.0000
7.000 1.6011 0.02237 0.01385 -0.1801 0.3870 1.0000
7.250 1.6207 0.02278 0.01428 -0.1789 0.3842 1.0000
7.500 1.6385 0.02321 0.01480 -0.1775 0.3808 1.0000
7.750 1.6563 0.02365 0.01530 -0.1760 0.3775 1.0000
8.000 1.6739 0.02411 0.01578 -0.1746 0.3744 1.0000
8.250 1.6920 0.02458 0.01625 -0.1733 0.3717 1.0000
8.500 1.7110 0.02506 0.01671 -0.1722 0.3692 1.0000
8.750 1.7270 0.02564 0.01739 -0.1707 0.3662 1.0000
9.000 1.7426 0.02624 0.01809 -0.1691 0.3630 1.0000
9.500 1.7729 0.02748 0.01944 -0.1660 0.3567 1.0000
9.750 1.7885 0.02810 0.02006 -0.1646 0.3538 1.0000
10.000 1.8023 0.02885 0.02088 -0.1630 0.3506 1.0000
10.250 1.8136 0.02972 0.02188 -0.1612 0.3465 1.0000
10.500 1.8246 0.03060 0.02282 -0.1593 0.3424 1.0000
10.750 1.8356 0.03147 0.02369 -0.1576 0.3383 1.0000
11.000 1.8450 0.03251 0.02481 -0.1557 0.3339 1.0000
11.250 1.8528 0.03370 0.02612 -0.1539 0.3289 1.0000
11.500 1.8608 0.03489 0.02735 -0.1521 0.3242 1.0000
11.750 1.8691 0.03609 0.02856 -0.1503 0.3201 1.0000
12.000 1.8742 0.03763 0.03025 -0.1486 0.3146 1.0000
12.250 1.8786 0.03921 0.03190 -0.1468 0.3093 1.0000
12.500 1.8834 0.04080 0.03350 -0.1451 0.3047 1.0000
12.750 1.8864 0.04271 0.03555 -0.1434 0.2992 1.0000
13.000 1.8880 0.04472 0.03763 -0.1418 0.2937 1.0000
13.250 1.8889 0.04686 0.03981 -0.1403 0.2884 1.0000
13.500 1.8882 0.04935 0.04242 -0.1389 0.2824 1.0000
13.750 1.8862 0.05196 0.04508 -0.1375 0.2767 1.0000
14.000 1.8837 0.05474 0.04794 -0.1362 0.2711 1.0000
14.250 1.8785 0.05792 0.05123 -0.1350 0.2647 1.0000
14.500 1.8711 0.06139 0.05471 -0.1339 0.2586 1.0000
14.750 1.8627 0.06522 0.05868 -0.1331 0.2519 1.0000
15.000 1.8507 0.06949 0.06299 -0.1323 0.2451 1.0000
15.250 1.8394 0.07388 0.06749 -0.1318 0.2387 1.0000
15.500 1.8254 0.07873 0.07242 -0.1315 0.2319 1.0000
15.750 1.8130 0.08345 0.07722 -0.1313 0.2263 1.0000
16.000 1.7999 0.08837 0.08226 -0.1314 0.2203 1.0000
16.250 1.7859 0.09337 0.08730 -0.1315 0.2144 1.0000
16.500 1.7729 0.09837 0.09242 -0.1318 0.2082 1.0000
16.750 1.7581 0.10363 0.09774 -0.1322 0.2016 1.0000
17.000 1.7450 0.10865 0.10284 -0.1327 0.1948 1.0000
17.250 1.7306 0.11392 0.10817 -0.1334 0.1870 1.0000
17.500 1.7168 0.11920 0.11353 -0.1343 0.1786 1.0000
17.750 1.7015 0.12475 0.11910 -0.1354 0.1684 1.0000
18.000 1.6842 0.13068 0.12502 -0.1369 0.1545 1.0000
18.250 1.6645 0.13704 0.13132 -0.1387 0.1395 1.0000
18.500 1.6444 0.14358 0.13779 -0.1408 0.1255 1.0000
18.750 1.6243 0.15028 0.14443 -0.1432 0.1123 1.0000
19.000 1.6050 0.15698 0.15107 -0.1459 0.0959 1.0000
19.250 1.5780 0.16512 0.15906 -0.1495 0.0642 1.0000
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