GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 50,000 Max Cl/Cd: 39.15 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe188-il-50000-n5.txt Download as CSV file: xf-goe188-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 -0.3471 0.10805 0.10165 -0.0246 1.0000 0.0736
-8.000 -0.3523 0.10663 0.10037 -0.0276 1.0000 0.0746
-7.750 -0.3542 0.10489 0.09874 -0.0325 1.0000 0.0751
-7.500 -0.3382 0.09845 0.09234 -0.0267 1.0000 0.0788
-7.250 -0.3334 0.09540 0.08936 -0.0271 1.0000 0.0823
-7.000 -0.3315 0.09278 0.08684 -0.0294 1.0000 0.0860
-6.750 -0.3326 0.09120 0.08535 -0.0354 1.0000 0.0890
-6.500 -0.3297 0.08773 0.08199 -0.0362 1.0000 0.0906
-6.250 -0.3241 0.08402 0.07838 -0.0323 1.0000 0.0948
-6.000 -0.3226 0.08161 0.07605 -0.0328 1.0000 0.0998
-5.750 -0.3245 0.08135 0.07568 -0.0390 1.0000 0.1042
-5.500 -0.3257 0.07695 0.07154 -0.0331 1.0000 0.1072
-5.250 -0.3269 0.07482 0.06947 -0.0311 1.0000 0.1123
-5.000 -0.3119 0.07147 0.06607 -0.0351 0.9954 0.1221
-4.750 -0.2839 0.06731 0.06184 -0.0398 0.9863 0.1384
-4.500 -0.2549 0.06344 0.05781 -0.0453 0.9766 0.1651
-4.250 -0.2314 0.05983 0.05422 -0.0472 0.9679 0.1976
-3.500 -0.1784 0.05124 0.04585 -0.0442 0.9417 0.3828
-3.000 -0.0041 0.04073 0.03274 -0.0738 0.9273 0.0719
-2.750 0.0348 0.03804 0.02957 -0.0755 0.9185 0.0578
-2.500 0.0790 0.03535 0.02631 -0.0781 0.9124 0.0500
-2.250 0.1157 0.03359 0.02407 -0.0791 0.9020 0.0457
-2.000 0.1534 0.03143 0.02152 -0.0806 0.8922 0.0439
-1.750 0.1942 0.02963 0.01928 -0.0821 0.8833 0.0444
-1.500 0.2290 0.02823 0.01751 -0.0826 0.8717 0.0452
-1.250 0.2624 0.02691 0.01591 -0.0827 0.8602 0.0451
-1.000 0.2949 0.02579 0.01451 -0.0824 0.8492 0.0452
-0.750 0.3277 0.02488 0.01330 -0.0823 0.8387 0.0463
-0.500 0.3585 0.02395 0.01218 -0.0822 0.8280 0.0512
-0.250 0.3865 0.02341 0.01141 -0.0818 0.8157 0.0563
0.000 0.4147 0.02303 0.01077 -0.0813 0.8035 0.0611
0.250 0.4429 0.02256 0.01024 -0.0810 0.7915 0.0792
0.500 0.4710 0.01989 0.00989 -0.0802 0.7806 1.0000
0.750 0.4986 0.02006 0.00954 -0.0795 0.7686 1.0000
1.000 0.5250 0.02024 0.00937 -0.0789 0.7559 1.0000
1.250 0.5507 0.02045 0.00931 -0.0782 0.7424 1.0000
1.500 0.5764 0.02067 0.00930 -0.0776 0.7289 1.0000
1.750 0.6020 0.02088 0.00932 -0.0770 0.7152 1.0000
2.000 0.6276 0.02108 0.00937 -0.0763 0.7013 1.0000
2.250 0.6532 0.02129 0.00945 -0.0757 0.6874 1.0000
2.500 0.6788 0.02150 0.00955 -0.0751 0.6733 1.0000
2.750 0.7043 0.02172 0.00968 -0.0744 0.6589 1.0000
3.000 0.7298 0.02196 0.00985 -0.0738 0.6445 1.0000
3.250 0.7551 0.02221 0.01005 -0.0732 0.6300 1.0000
3.500 0.7804 0.02249 0.01029 -0.0726 0.6154 1.0000
3.750 0.8056 0.02279 0.01059 -0.0720 0.6008 1.0000
4.000 0.8306 0.02312 0.01092 -0.0715 0.5865 1.0000
4.250 0.8554 0.02347 0.01128 -0.0709 0.5722 1.0000
4.500 0.8802 0.02385 0.01172 -0.0704 0.5584 1.0000
4.750 0.9048 0.02425 0.01216 -0.0699 0.5449 1.0000
5.000 0.9294 0.02466 0.01262 -0.0693 0.5318 1.0000
5.250 0.9540 0.02507 0.01313 -0.0688 0.5192 1.0000
5.500 0.9785 0.02547 0.01359 -0.0681 0.5064 1.0000
5.750 1.0028 0.02586 0.01404 -0.0675 0.4935 1.0000
6.000 1.0268 0.02629 0.01460 -0.0668 0.4806 1.0000
6.250 1.0500 0.02682 0.01526 -0.0662 0.4676 1.0000
6.500 1.0732 0.02743 0.01602 -0.0655 0.4554 1.0000
6.750 1.0965 0.02807 0.01682 -0.0649 0.4442 1.0000
7.000 1.1203 0.02869 0.01764 -0.0643 0.4336 1.0000
7.250 1.1444 0.02934 0.01846 -0.0638 0.4231 1.0000
7.500 1.1658 0.03019 0.01958 -0.0631 0.4118 1.0000
7.750 1.1878 0.03105 0.02070 -0.0624 0.4011 1.0000
8.000 1.2108 0.03184 0.02178 -0.0617 0.3908 1.0000
8.250 1.2330 0.03262 0.02281 -0.0609 0.3791 1.0000
8.500 1.2522 0.03333 0.02376 -0.0596 0.3641 1.0000
8.750 1.2661 0.03411 0.02484 -0.0577 0.3458 1.0000
9.000 1.2788 0.03478 0.02577 -0.0557 0.3262 1.0000
9.250 1.2920 0.03552 0.02677 -0.0537 0.3087 1.0000
9.500 1.3044 0.03638 0.02793 -0.0517 0.2924 1.0000
9.750 1.3111 0.03743 0.02939 -0.0493 0.2735 1.0000
10.000 1.3075 0.03855 0.03066 -0.0459 0.2459 1.0000
10.250 1.2970 0.04018 0.03230 -0.0422 0.2144 1.0000
10.500 1.2859 0.04249 0.03447 -0.0395 0.1821 1.0000
10.750 1.2751 0.04555 0.03741 -0.0378 0.1524 1.0000
11.000 1.2633 0.04931 0.04110 -0.0369 0.1201 1.0000
11.250 1.2480 0.05380 0.04542 -0.0367 0.0961 1.0000
11.500 1.2318 0.05878 0.05028 -0.0370 0.0810 1.0000
11.750 1.2161 0.06399 0.05547 -0.0377 0.0713 1.0000
12.000 1.2022 0.06924 0.06081 -0.0385 0.0626 1.0000
12.250 1.1863 0.07488 0.06646 -0.0397 0.0574 1.0000
12.500 1.1742 0.08018 0.07189 -0.0408 0.0507 1.0000
12.750 1.1610 0.08571 0.07748 -0.0422 0.0466 1.0000
13.000 1.1501 0.09097 0.08280 -0.0434 0.0425 1.0000
13.250 1.1414 0.09602 0.08796 -0.0446 0.0387 1.0000
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Polar data table (+)
Polar graphs
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