GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 200,000 Max Cl/Cd: 80.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe501-il-200000-n5.txt Download as CSV file: xf-goe501-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 501 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1442 0.09858 0.09459 -0.0897 0.9633 0.0369
-10.500 -0.1393 0.09270 0.08869 -0.0950 0.9605 0.0383
-10.250 -0.1389 0.08486 0.08082 -0.1023 0.9581 0.0395
-10.000 -0.1207 0.08425 0.08022 -0.1027 0.9521 0.0403
-9.750 -0.1046 0.08132 0.07728 -0.1060 0.9480 0.0412
-9.250 -0.2644 0.03128 0.02596 -0.1607 0.8987 0.0454
-9.000 -0.2432 0.03013 0.02478 -0.1612 0.8928 0.0462
-8.750 -0.2203 0.02903 0.02357 -0.1620 0.8869 0.0470
-8.500 -0.1942 0.02752 0.02185 -0.1636 0.8829 0.0479
-8.250 -0.1708 0.02606 0.02016 -0.1646 0.8776 0.0489
-8.000 -0.1469 0.02472 0.01856 -0.1654 0.8718 0.0503
-7.750 -0.1193 0.02331 0.01677 -0.1666 0.8677 0.0518
-7.500 -0.0919 0.02208 0.01526 -0.1675 0.8636 0.0528
-7.250 -0.0676 0.02127 0.01439 -0.1674 0.8573 0.0537
-7.000 -0.0392 0.02051 0.01354 -0.1679 0.8525 0.0548
-6.750 -0.0103 0.01982 0.01272 -0.1684 0.8477 0.0562
-6.500 0.0153 0.01922 0.01198 -0.1682 0.8411 0.0578
-6.250 0.0444 0.01857 0.01113 -0.1686 0.8363 0.0595
-6.000 0.0736 0.01798 0.01035 -0.1690 0.8316 0.0607
-5.750 0.0990 0.01731 0.00967 -0.1688 0.8252 0.0621
-5.500 0.1275 0.01679 0.00912 -0.1690 0.8204 0.0637
-5.250 0.1570 0.01634 0.00858 -0.1694 0.8161 0.0658
-5.000 0.1829 0.01599 0.00816 -0.1691 0.8093 0.0680
-4.750 0.2116 0.01563 0.00766 -0.1692 0.8038 0.0698
-4.500 0.2406 0.01513 0.00712 -0.1694 0.7993 0.0718
-4.250 0.2668 0.01479 0.00679 -0.1692 0.7935 0.0743
-4.000 0.2949 0.01450 0.00645 -0.1693 0.7885 0.0773
-3.750 0.3245 0.01423 0.00608 -0.1696 0.7843 0.0802
-3.500 0.3515 0.01397 0.00580 -0.1694 0.7789 0.0830
-3.250 0.3789 0.01371 0.00554 -0.1694 0.7733 0.0873
-3.000 0.4081 0.01351 0.00526 -0.1695 0.7686 0.0923
-2.750 0.4360 0.01330 0.00509 -0.1695 0.7633 0.0993
-2.500 0.4631 0.01313 0.00498 -0.1694 0.7572 0.1117
-2.250 0.4917 0.01297 0.00487 -0.1695 0.7519 0.1375
-2.000 0.5198 0.01287 0.00477 -0.1694 0.7463 0.1599
-1.750 0.5464 0.01279 0.00472 -0.1691 0.7396 0.1770
-1.500 0.5750 0.01270 0.00462 -0.1691 0.7337 0.1952
-1.250 0.6019 0.01265 0.00461 -0.1689 0.7272 0.2133
-1.000 0.6289 0.01259 0.00460 -0.1686 0.7200 0.2338
-0.750 0.6566 0.01255 0.00456 -0.1684 0.7124 0.2550
-0.500 0.6825 0.01253 0.00458 -0.1679 0.7025 0.2778
-0.250 0.7091 0.01252 0.00458 -0.1675 0.6934 0.2992
0.000 0.7353 0.01252 0.00459 -0.1670 0.6832 0.3196
0.250 0.7608 0.01253 0.00464 -0.1664 0.6722 0.3404
0.500 0.7866 0.01255 0.00465 -0.1659 0.6606 0.3595
0.750 0.8119 0.01257 0.00466 -0.1653 0.6473 0.3776
1.000 0.8366 0.01260 0.00469 -0.1645 0.6321 0.3947
1.250 0.8613 0.01264 0.00472 -0.1638 0.6160 0.4112
1.500 0.8855 0.01271 0.00475 -0.1629 0.5990 0.4274
1.750 0.9093 0.01281 0.00481 -0.1620 0.5817 0.4457
2.000 0.9324 0.01294 0.00490 -0.1610 0.5653 0.4672
2.500 0.9786 0.01325 0.00523 -0.1591 0.5396 0.5330
2.750 1.0019 0.01339 0.00543 -0.1581 0.5302 0.5814
3.000 1.0251 0.01350 0.00563 -0.1572 0.5211 0.6358
3.250 1.0471 0.01348 0.00582 -0.1559 0.5131 0.7348
3.750 1.0955 0.01369 0.00615 -0.1543 0.4981 1.0000
4.000 1.1199 0.01393 0.00637 -0.1537 0.4912 1.0000
4.250 1.1438 0.01422 0.00661 -0.1530 0.4845 1.0000
4.500 1.1676 0.01450 0.00686 -0.1523 0.4779 1.0000
4.750 1.1904 0.01478 0.00711 -0.1514 0.4699 1.0000
5.000 1.2129 0.01509 0.00738 -0.1504 0.4628 1.0000
5.250 1.2358 0.01535 0.00766 -0.1496 0.4561 1.0000
5.500 1.2583 0.01565 0.00795 -0.1486 0.4502 1.0000
5.750 1.2807 0.01595 0.00825 -0.1477 0.4448 1.0000
6.000 1.3026 0.01622 0.00857 -0.1466 0.4388 1.0000
6.250 1.3228 0.01653 0.00887 -0.1453 0.4326 1.0000
6.500 1.3420 0.01684 0.00921 -0.1438 0.4253 1.0000
6.750 1.3597 0.01718 0.00956 -0.1420 0.4168 1.0000
7.000 1.3771 0.01753 0.00994 -0.1402 0.4081 1.0000
7.250 1.3918 0.01796 0.01034 -0.1380 0.3971 1.0000
7.500 1.4072 0.01837 0.01079 -0.1360 0.3851 1.0000
7.750 1.4220 0.01884 0.01126 -0.1339 0.3735 1.0000
8.000 1.4361 0.01936 0.01178 -0.1318 0.3628 1.0000
8.250 1.4497 0.01992 0.01234 -0.1296 0.3490 1.0000
8.500 1.4613 0.02057 0.01299 -0.1273 0.3329 1.0000
8.750 1.4715 0.02134 0.01372 -0.1248 0.3154 1.0000
9.000 1.4804 0.02221 0.01455 -0.1223 0.2942 1.0000
9.250 1.4850 0.02336 0.01559 -0.1193 0.2686 1.0000
9.500 1.4867 0.02477 0.01686 -0.1162 0.2398 1.0000
9.750 1.4886 0.02629 0.01826 -0.1133 0.2173 1.0000
10.000 1.4923 0.02779 0.01971 -0.1108 0.2029 1.0000
10.250 1.4968 0.02930 0.02119 -0.1085 0.1930 1.0000
10.500 1.5025 0.03079 0.02268 -0.1064 0.1853 1.0000
10.750 1.5079 0.03235 0.02425 -0.1045 0.1798 1.0000
11.000 1.5169 0.03370 0.02567 -0.1029 0.1748 1.0000
11.250 1.5236 0.03526 0.02729 -0.1012 0.1699 1.0000
11.500 1.5277 0.03707 0.02912 -0.0995 0.1654 1.0000
11.750 1.5368 0.03853 0.03068 -0.0982 0.1613 1.0000
12.000 1.5454 0.04006 0.03231 -0.0969 0.1566 1.0000
12.250 1.5500 0.04198 0.03428 -0.0955 0.1514 1.0000
12.500 1.5559 0.04385 0.03623 -0.0943 0.1454 1.0000
12.750 1.5635 0.04561 0.03809 -0.0933 0.1374 1.0000
13.000 1.5693 0.04759 0.04014 -0.0923 0.1287 1.0000
13.250 1.5743 0.04972 0.04231 -0.0914 0.1165 1.0000
13.500 1.5749 0.05236 0.04492 -0.0905 0.1008 1.0000
13.750 1.5720 0.05548 0.04798 -0.0896 0.0909 1.0000
14.000 1.5684 0.05879 0.05127 -0.0889 0.0842 1.0000
14.250 1.5667 0.06198 0.05452 -0.0884 0.0792 1.0000
14.500 1.5630 0.06552 0.05809 -0.0880 0.0752 1.0000
14.750 1.5634 0.06863 0.06130 -0.0878 0.0720 1.0000
15.000 1.5636 0.07184 0.06461 -0.0877 0.0690 1.0000
15.250 1.5616 0.07542 0.06827 -0.0877 0.0664 1.0000
15.500 1.5579 0.07934 0.07227 -0.0880 0.0641 1.0000
15.750 1.5600 0.08248 0.07553 -0.0882 0.0617 1.0000
16.000 1.5604 0.08590 0.07908 -0.0886 0.0592 1.0000
16.250 1.5586 0.08970 0.08297 -0.0891 0.0568 1.0000
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