GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 500,000 Max Cl/Cd: 106.74 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe502-il-500000.txt Download as CSV file: xf-goe502-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4054 0.04910 0.04577 -0.1380 0.9648 0.0432
-11.500 -0.4335 0.03552 0.03165 -0.1627 0.9547 0.0430
-11.250 -0.4263 0.03214 0.02801 -0.1674 0.9462 0.0432
-11.000 -0.4029 0.02956 0.02519 -0.1718 0.9420 0.0436
-10.750 -0.3742 0.02744 0.02284 -0.1757 0.9388 0.0441
-10.500 -0.3601 0.02615 0.02138 -0.1753 0.9298 0.0445
-10.250 -0.3326 0.02476 0.01975 -0.1772 0.9244 0.0450
-10.000 -0.3119 0.02371 0.01850 -0.1773 0.9165 0.0454
-9.750 -0.2881 0.02286 0.01743 -0.1775 0.9087 0.0457
-9.500 -0.2644 0.02121 0.01567 -0.1779 0.9018 0.0461
-9.250 -0.2439 0.02017 0.01461 -0.1771 0.8932 0.0466
-9.000 -0.2160 0.01935 0.01372 -0.1777 0.8871 0.0472
-8.750 -0.1959 0.01872 0.01304 -0.1766 0.8783 0.0476
-8.500 -0.1706 0.01807 0.01231 -0.1764 0.8706 0.0482
-8.250 -0.1472 0.01748 0.01166 -0.1758 0.8622 0.0488
-8.000 -0.1232 0.01692 0.01101 -0.1753 0.8533 0.0495
-7.750 -0.0979 0.01644 0.01043 -0.1749 0.8452 0.0502
-7.500 -0.0735 0.01607 0.00995 -0.1743 0.8355 0.0508
-7.250 -0.0489 0.01542 0.00921 -0.1739 0.8269 0.0515
-7.000 -0.0258 0.01470 0.00849 -0.1732 0.8171 0.0523
-6.750 -0.0006 0.01422 0.00798 -0.1728 0.8088 0.0531
-6.500 0.0241 0.01381 0.00753 -0.1723 0.7998 0.0539
-6.250 0.0503 0.01345 0.00709 -0.1719 0.7920 0.0549
-6.000 0.0755 0.01313 0.00671 -0.1714 0.7835 0.0558
-5.750 0.1022 0.01288 0.00635 -0.1711 0.7759 0.0567
-5.500 0.1268 0.01244 0.00588 -0.1706 0.7686 0.0578
-5.250 0.1523 0.01205 0.00547 -0.1702 0.7617 0.0593
-5.000 0.1792 0.01180 0.00515 -0.1700 0.7554 0.0608
-4.750 0.2049 0.01157 0.00488 -0.1695 0.7486 0.0623
-4.500 0.2317 0.01139 0.00462 -0.1692 0.7420 0.0636
-4.250 0.2585 0.01110 0.00429 -0.1690 0.7360 0.0659
-4.000 0.2845 0.01088 0.00406 -0.1685 0.7300 0.0684
-3.750 0.3113 0.01071 0.00384 -0.1682 0.7238 0.0719
-3.500 0.3391 0.01055 0.00365 -0.1681 0.7176 0.0788
-3.250 0.3642 0.01024 0.00351 -0.1676 0.7116 0.1079
-3.000 0.3905 0.01006 0.00342 -0.1672 0.7055 0.1395
-2.750 0.4182 0.01000 0.00337 -0.1670 0.6993 0.1617
-2.500 0.4442 0.00993 0.00335 -0.1665 0.6931 0.1767
-2.250 0.4705 0.00988 0.00332 -0.1660 0.6863 0.1903
-2.000 0.4979 0.00991 0.00329 -0.1657 0.6799 0.2016
-1.750 0.5237 0.00986 0.00329 -0.1652 0.6733 0.2135
-1.500 0.5497 0.00983 0.00327 -0.1646 0.6659 0.2248
-1.250 0.5764 0.00989 0.00327 -0.1642 0.6589 0.2370
-1.000 0.6016 0.00983 0.00328 -0.1634 0.6512 0.2481
-0.750 0.6273 0.00986 0.00326 -0.1628 0.6433 0.2582
-0.500 0.6527 0.00986 0.00328 -0.1621 0.6352 0.2692
-0.250 0.6778 0.00988 0.00328 -0.1614 0.6263 0.2791
0.000 0.7029 0.00991 0.00331 -0.1606 0.6182 0.2897
0.250 0.7277 0.00994 0.00332 -0.1598 0.6090 0.2990
0.500 0.7521 0.00999 0.00335 -0.1590 0.6005 0.3089
0.750 0.7767 0.01005 0.00338 -0.1581 0.5915 0.3181
1.000 0.8008 0.01011 0.00344 -0.1572 0.5835 0.3291
1.250 0.8255 0.01017 0.00350 -0.1565 0.5754 0.3399
1.500 0.8493 0.01026 0.00357 -0.1555 0.5676 0.3513
1.750 0.8739 0.01034 0.00365 -0.1548 0.5605 0.3618
2.000 0.8981 0.01042 0.00374 -0.1539 0.5536 0.3739
2.250 0.9221 0.01056 0.00385 -0.1531 0.5471 0.3869
2.500 0.9466 0.01062 0.00396 -0.1523 0.5410 0.4019
2.750 0.9704 0.01072 0.00408 -0.1514 0.5347 0.4181
3.000 0.9947 0.01088 0.00423 -0.1506 0.5289 0.4359
3.250 1.0187 0.01093 0.00437 -0.1497 0.5239 0.4551
3.500 1.0420 0.01101 0.00450 -0.1488 0.5182 0.4765
3.750 1.0646 0.01116 0.00464 -0.1477 0.5120 0.4998
4.000 1.0858 0.01120 0.00479 -0.1463 0.5059 0.5281
4.250 1.1059 0.01120 0.00494 -0.1447 0.4999 0.5737
4.500 1.1244 0.01113 0.00517 -0.1428 0.4945 0.6990
4.750 1.1593 0.01092 0.00542 -0.1442 0.4889 1.0000
5.000 1.1804 0.01106 0.00556 -0.1428 0.4834 1.0000
5.250 1.2008 0.01126 0.00571 -0.1413 0.4773 1.0000
5.500 1.2228 0.01152 0.00590 -0.1401 0.4719 1.0000
5.750 1.2439 0.01166 0.00608 -0.1388 0.4673 1.0000
6.000 1.2649 0.01185 0.00626 -0.1374 0.4621 1.0000
6.250 1.2847 0.01210 0.00646 -0.1359 0.4563 1.0000
6.500 1.3047 0.01231 0.00668 -0.1344 0.4507 1.0000
6.750 1.3246 0.01251 0.00689 -0.1329 0.4449 1.0000
7.000 1.3434 0.01277 0.00712 -0.1313 0.4391 1.0000
7.250 1.3626 0.01304 0.00738 -0.1297 0.4335 1.0000
7.500 1.3824 0.01326 0.00763 -0.1283 0.4280 1.0000
7.750 1.4008 0.01354 0.00790 -0.1266 0.4223 1.0000
8.000 1.4179 0.01388 0.00822 -0.1248 0.4160 1.0000
8.250 1.4358 0.01415 0.00852 -0.1232 0.4086 1.0000
8.500 1.4506 0.01456 0.00889 -0.1210 0.4014 1.0000
8.750 1.4683 0.01488 0.00925 -0.1194 0.3941 1.0000
9.000 1.4840 0.01529 0.00965 -0.1175 0.3868 1.0000
9.250 1.4994 0.01574 0.01009 -0.1156 0.3799 1.0000
9.500 1.5154 0.01617 0.01055 -0.1139 0.3719 1.0000
9.750 1.5280 0.01675 0.01111 -0.1117 0.3637 1.0000
10.000 1.5422 0.01729 0.01166 -0.1098 0.3535 1.0000
10.250 1.5544 0.01795 0.01230 -0.1077 0.3446 1.0000
10.500 1.5657 0.01867 0.01301 -0.1055 0.3337 1.0000
10.750 1.5769 0.01943 0.01376 -0.1034 0.3224 1.0000
11.000 1.5850 0.02038 0.01467 -0.1010 0.3097 1.0000
11.250 1.5915 0.02146 0.01571 -0.0985 0.2960 1.0000
11.500 1.5959 0.02273 0.01693 -0.0960 0.2800 1.0000
11.750 1.5994 0.02411 0.01826 -0.0934 0.2635 1.0000
12.000 1.6010 0.02570 0.01978 -0.0909 0.2455 1.0000
12.250 1.5999 0.02757 0.02157 -0.0883 0.2266 1.0000
12.500 1.5974 0.02964 0.02356 -0.0858 0.2094 1.0000
12.750 1.5957 0.03177 0.02565 -0.0836 0.1958 1.0000
13.000 1.5943 0.03398 0.02782 -0.0816 0.1851 1.0000
13.250 1.5958 0.03602 0.02986 -0.0800 0.1768 1.0000
13.500 1.5968 0.03819 0.03203 -0.0784 0.1703 1.0000
13.750 1.6001 0.04021 0.03407 -0.0771 0.1647 1.0000
14.000 1.5993 0.04263 0.03649 -0.0757 0.1593 1.0000
14.250 1.6044 0.04457 0.03849 -0.0747 0.1548 1.0000
14.500 1.6070 0.04679 0.04074 -0.0736 0.1501 1.0000
14.750 1.6058 0.04942 0.04339 -0.0725 0.1455 1.0000
15.000 1.6104 0.05153 0.04556 -0.0717 0.1415 1.0000
15.250 1.6137 0.05381 0.04789 -0.0710 0.1371 1.0000
15.500 1.6116 0.05672 0.05080 -0.0702 0.1325 1.0000
15.750 1.6152 0.05908 0.05324 -0.0697 0.1282 1.0000
16.000 1.6166 0.06173 0.05592 -0.0692 0.1232 1.0000
16.250 1.6138 0.06488 0.05909 -0.0688 0.1182 1.0000
16.500 1.6157 0.06757 0.06183 -0.0685 0.1125 1.0000
16.750 1.6110 0.07111 0.06538 -0.0683 0.1068 1.0000
17.000 1.6104 0.07418 0.06849 -0.0682 0.1004 1.0000
17.250 1.6055 0.07784 0.07217 -0.0682 0.0940 1.0000
17.500 1.5987 0.08181 0.07614 -0.0683 0.0881 1.0000
17.750 1.5953 0.08537 0.07973 -0.0685 0.0828 1.0000
18.000 1.5882 0.08950 0.08387 -0.0689 0.0784 1.0000
18.250 1.5851 0.09312 0.08754 -0.0693 0.0750 1.0000
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Polar data table (+)
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