GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 50,000 Max Cl/Cd: 40.04 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe113-il-50000-n5.txt Download as CSV file: xf-goe113-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4494 0.10959 0.10293 -0.0107 1.0000 0.0693
-8.000 -0.4524 0.10775 0.10121 -0.0146 1.0000 0.0701
-7.750 -0.4503 0.10531 0.09884 -0.0205 1.0000 0.0706
-7.500 -0.4363 0.09859 0.09214 -0.0133 1.0000 0.0745
-7.250 -0.4305 0.09522 0.08882 -0.0146 1.0000 0.0782
-7.000 -0.4258 0.09223 0.08590 -0.0191 1.0000 0.0826
-6.750 -0.4184 0.09008 0.08372 -0.0294 1.0000 0.0848
-6.500 -0.4109 0.08456 0.07833 -0.0232 1.0000 0.0886
-6.250 -0.4015 0.08117 0.07495 -0.0253 1.0000 0.0953
-6.000 -0.3919 0.07737 0.07117 -0.0291 1.0000 0.1016
-5.500 -0.3661 0.07157 0.06512 -0.0368 1.0000 0.1281
-5.250 -0.3566 0.06749 0.06114 -0.0359 1.0000 0.1432
-5.000 -0.3465 0.06369 0.05741 -0.0348 1.0000 0.1590
-4.750 -0.3344 0.06022 0.05397 -0.0343 1.0000 0.1752
-4.500 -0.3207 0.05699 0.05074 -0.0341 1.0000 0.1946
-4.250 -0.2610 0.04918 0.04200 -0.0436 1.0000 0.0658
-4.000 -0.2329 0.04509 0.03745 -0.0450 1.0000 0.0543
-3.750 -0.2099 0.04162 0.03371 -0.0455 1.0000 0.0525
-3.500 -0.1843 0.03861 0.03026 -0.0460 1.0000 0.0541
-3.250 -0.1582 0.03580 0.02696 -0.0462 1.0000 0.0550
-3.000 -0.1325 0.03304 0.02374 -0.0461 1.0000 0.0545
-2.750 -0.1060 0.03063 0.02084 -0.0458 1.0000 0.0548
-2.500 -0.0814 0.02853 0.01845 -0.0457 1.0000 0.0606
-2.250 -0.0557 0.02678 0.01635 -0.0452 1.0000 0.0639
-2.000 -0.0296 0.02521 0.01440 -0.0445 1.0000 0.0658
-1.750 -0.0049 0.02403 0.01293 -0.0440 1.0000 0.0738
-1.500 0.0190 0.02302 0.01172 -0.0432 1.0000 0.0781
-1.250 0.0439 0.02224 0.01069 -0.0425 1.0000 0.0795
-1.000 0.0689 0.02168 0.00990 -0.0422 0.9995 0.0810
-0.750 0.1129 0.02105 0.00897 -0.0455 0.9882 0.0839
-0.500 0.1557 0.02048 0.00821 -0.0489 0.9751 0.0892
-0.250 0.1988 0.02002 0.00766 -0.0522 0.9619 0.1018
0.000 0.2343 0.01701 0.00732 -0.0538 0.9492 1.0000
0.250 0.2748 0.01716 0.00697 -0.0563 0.9328 1.0000
0.500 0.3152 0.01728 0.00679 -0.0589 0.9174 1.0000
0.750 0.3538 0.01738 0.00668 -0.0611 0.9017 1.0000
1.000 0.3902 0.01748 0.00662 -0.0627 0.8853 1.0000
1.250 0.4245 0.01761 0.00664 -0.0639 0.8681 1.0000
1.500 0.4582 0.01773 0.00669 -0.0650 0.8516 1.0000
1.750 0.4912 0.01785 0.00676 -0.0658 0.8350 1.0000
2.000 0.5236 0.01793 0.00679 -0.0662 0.8171 1.0000
2.250 0.5522 0.01806 0.00688 -0.0658 0.7949 1.0000
2.500 0.5807 0.01813 0.00693 -0.0651 0.7713 1.0000
2.750 0.6071 0.01825 0.00699 -0.0639 0.7457 1.0000
3.000 0.6324 0.01845 0.00719 -0.0629 0.7214 1.0000
3.250 0.6585 0.01868 0.00747 -0.0620 0.7011 1.0000
3.500 0.6834 0.01897 0.00783 -0.0611 0.6795 1.0000
3.750 0.7086 0.01922 0.00813 -0.0601 0.6578 1.0000
4.000 0.7324 0.01949 0.00849 -0.0589 0.6316 1.0000
4.250 0.7561 0.01977 0.00888 -0.0576 0.6030 1.0000
4.500 0.7796 0.02005 0.00924 -0.0563 0.5723 1.0000
4.750 0.8028 0.02038 0.00967 -0.0550 0.5399 1.0000
5.000 0.8258 0.02076 0.01020 -0.0538 0.5048 1.0000
5.250 0.8485 0.02119 0.01081 -0.0525 0.4670 1.0000
5.500 0.8668 0.02170 0.01115 -0.0505 0.3972 1.0000
5.750 0.8867 0.02243 0.01173 -0.0490 0.3402 1.0000
6.000 0.9036 0.02359 0.01247 -0.0475 0.2712 1.0000
6.250 0.9241 0.02463 0.01353 -0.0465 0.2345 1.0000
6.500 0.9407 0.02624 0.01467 -0.0455 0.1319 1.0000
7.000 0.9695 0.03086 0.01876 -0.0424 0.0385 1.0000
7.250 0.9854 0.03276 0.02090 -0.0409 0.0344 1.0000
7.500 1.0005 0.03465 0.02304 -0.0394 0.0307 1.0000
7.750 1.0121 0.03685 0.02542 -0.0377 0.0284 1.0000
8.000 1.0251 0.03886 0.02773 -0.0358 0.0275 1.0000
8.250 1.0381 0.04099 0.03014 -0.0339 0.0268 1.0000
8.500 1.0523 0.04325 0.03267 -0.0321 0.0262 1.0000
8.750 1.0682 0.04572 0.03544 -0.0304 0.0257 1.0000
9.000 1.0836 0.04846 0.03850 -0.0288 0.0249 1.0000
9.250 1.0961 0.05144 0.04183 -0.0273 0.0240 1.0000
9.500 1.1046 0.05462 0.04535 -0.0258 0.0231 1.0000
9.750 1.1090 0.05800 0.04921 -0.0242 0.0226 1.0000
10.000 1.1087 0.06151 0.05307 -0.0225 0.0223 1.0000
10.250 1.1028 0.06505 0.05693 -0.0207 0.0223 1.0000
10.500 1.0933 0.06889 0.06109 -0.0196 0.0223 1.0000
10.750 1.0805 0.07318 0.06568 -0.0195 0.0225 1.0000
11.000 1.0657 0.07808 0.07084 -0.0207 0.0226 1.0000
11.250 1.0494 0.08369 0.07670 -0.0233 0.0228 1.0000
11.500 1.0322 0.09012 0.08334 -0.0271 0.0230 1.0000
11.750 1.0143 0.09746 0.09085 -0.0319 0.0233 1.0000
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Polar data table (+)
Polar graphs
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