GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 50,000 Max Cl/Cd: 34.11 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe406-il-50000-n5.txt Download as CSV file: xf-goe406-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2770 0.11834 0.11181 -0.0324 1.0000 0.0996
-8.750 -0.2857 0.11714 0.11071 -0.0300 1.0000 0.1015
-8.500 -0.2975 0.11629 0.10998 -0.0276 1.0000 0.1025
-8.250 -0.2865 0.11351 0.10720 -0.0336 0.9913 0.1070
-8.000 -0.2924 0.11263 0.10635 -0.0417 0.9777 0.1089
-7.750 -0.2746 0.10779 0.10153 -0.0444 0.9717 0.1103
-7.500 -0.2501 0.10305 0.09677 -0.0442 0.9662 0.1132
-7.250 -0.2348 0.09971 0.09341 -0.0472 0.9590 0.1166
-7.000 -0.2312 0.09729 0.09101 -0.0494 0.9475 0.1199
-6.750 -0.2334 0.09562 0.08929 -0.0559 0.9327 0.1241
-6.250 -0.2081 0.08822 0.08189 -0.0579 0.9174 0.1280
-6.000 -0.1958 0.08531 0.07897 -0.0583 0.9097 0.1319
-5.750 -0.1888 0.08390 0.07734 -0.0655 0.8991 0.1407
-5.500 -0.1816 0.08017 0.07372 -0.0631 0.8910 0.1430
-5.250 -0.1624 0.07696 0.07051 -0.0632 0.8859 0.1495
-5.000 -0.1594 0.07520 0.06859 -0.0655 0.8755 0.1585
-4.750 -0.1396 0.07176 0.06519 -0.0651 0.8710 0.1638
-4.250 -0.1151 0.06696 0.06026 -0.0658 0.8565 0.1808
-4.000 -0.1031 0.06480 0.05799 -0.0661 0.8496 0.1947
-3.750 -0.0923 0.06303 0.05612 -0.0656 0.8419 0.2111
-3.250 -0.0325 0.05536 0.04725 -0.0698 0.8284 0.0935
-3.000 -0.0093 0.05276 0.04453 -0.0700 0.8234 0.0905
-2.750 0.0091 0.05073 0.04227 -0.0691 0.8171 0.0878
-2.500 0.0269 0.04912 0.04005 -0.0672 0.8092 0.0819
-2.250 0.0557 0.04679 0.03757 -0.0678 0.8050 0.0803
-2.000 0.0662 0.04565 0.03626 -0.0651 0.7959 0.0790
-1.750 0.0943 0.04376 0.03406 -0.0649 0.7897 0.0771
-1.500 0.1218 0.04201 0.03194 -0.0643 0.7823 0.0756
-1.250 0.1466 0.04054 0.03010 -0.0631 0.7728 0.0743
-1.000 0.1945 0.03835 0.02750 -0.0655 0.7680 0.0745
-0.750 0.2055 0.03780 0.02678 -0.0622 0.7552 0.0755
-0.500 0.2555 0.03598 0.02459 -0.0651 0.7504 0.0776
-0.250 0.2666 0.03564 0.02407 -0.0619 0.7381 0.0780
0.000 0.3171 0.03408 0.02218 -0.0650 0.7333 0.0787
0.250 0.3319 0.03382 0.02178 -0.0625 0.7216 0.0793
0.500 0.4006 0.03237 0.01992 -0.0691 0.7164 0.0822
0.750 0.4311 0.03196 0.01952 -0.0697 0.7054 0.0863
1.000 0.4855 0.03084 0.01822 -0.0738 0.6987 0.0925
1.250 0.5073 0.03072 0.01803 -0.0726 0.6869 0.0957
1.500 0.5565 0.02968 0.01692 -0.0757 0.6801 0.1057
1.750 0.5752 0.02965 0.01692 -0.0741 0.6669 0.1173
2.000 0.6061 0.02922 0.01658 -0.0744 0.6557 0.1463
2.250 0.7532 0.02643 0.01526 -0.0976 0.6455 1.0000
2.500 0.7683 0.02676 0.01546 -0.0950 0.6312 1.0000
2.750 0.7861 0.02700 0.01557 -0.0929 0.6173 1.0000
3.000 0.8066 0.02717 0.01561 -0.0912 0.6038 1.0000
3.250 0.8299 0.02724 0.01555 -0.0899 0.5908 1.0000
3.500 0.8545 0.02727 0.01544 -0.0889 0.5778 1.0000
3.750 0.8714 0.02760 0.01568 -0.0867 0.5628 1.0000
4.000 0.8893 0.02794 0.01594 -0.0848 0.5485 1.0000
4.250 0.9089 0.02827 0.01618 -0.0832 0.5352 1.0000
4.500 0.9309 0.02852 0.01631 -0.0819 0.5227 1.0000
4.750 0.9553 0.02870 0.01636 -0.0811 0.5113 1.0000
5.000 0.9717 0.02926 0.01689 -0.0791 0.4989 1.0000
5.250 0.9923 0.02971 0.01725 -0.0778 0.4884 1.0000
5.500 1.0164 0.03004 0.01749 -0.0771 0.4792 1.0000
5.750 1.0331 0.03073 0.01818 -0.0754 0.4697 1.0000
6.000 1.0596 0.03106 0.01841 -0.0751 0.4621 1.0000
6.250 1.0740 0.03189 0.01927 -0.0731 0.4534 1.0000
6.500 1.0990 0.03233 0.01967 -0.0726 0.4464 1.0000
6.750 1.1151 0.03317 0.02055 -0.0710 0.4394 1.0000
7.000 1.1342 0.03390 0.02131 -0.0698 0.4330 1.0000
7.250 1.1644 0.03431 0.02167 -0.0703 0.4282 1.0000
7.500 1.1718 0.03556 0.02309 -0.0676 0.4221 1.0000
7.750 1.1892 0.03643 0.02402 -0.0662 0.4167 1.0000
8.000 1.2186 0.03692 0.02450 -0.0666 0.4122 1.0000
8.250 1.2233 0.03829 0.02604 -0.0636 0.4069 1.0000
8.500 1.2317 0.03952 0.02740 -0.0611 0.4020 1.0000
8.750 1.2523 0.04041 0.02837 -0.0604 0.3981 1.0000
9.000 1.2856 0.04098 0.02898 -0.0614 0.3947 1.0000
9.250 1.2688 0.04320 0.03142 -0.0558 0.3903 1.0000
9.500 1.2643 0.04514 0.03354 -0.0522 0.3858 1.0000
9.750 1.2785 0.04633 0.03485 -0.0508 0.3818 1.0000
10.000 1.3102 0.04685 0.03545 -0.0514 0.3786 1.0000
10.250 1.2810 0.05033 0.03913 -0.0459 0.3745 1.0000
10.500 1.2261 0.05639 0.04538 -0.0402 0.3689 1.0000
10.750 1.2226 0.05927 0.04838 -0.0385 0.3648 1.0000
11.000 1.2567 0.05901 0.04824 -0.0384 0.3621 1.0000
11.250 1.0919 0.08038 0.06963 -0.0368 0.3471 1.0000
11.500 1.1134 0.08085 0.07024 -0.0358 0.3449 1.0000
12.000 1.0520 0.09672 0.08624 -0.0379 0.3283 1.0000
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Polar data table (+)
Polar graphs
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