GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 100,000 Max Cl/Cd: 49.97 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe654-il-100000-n5.txt Download as CSV file: xf-goe654-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1954 0.10171 0.09718 -0.0472 0.9785 0.0809
-9.000 -0.2013 0.09742 0.09293 -0.0586 0.9572 0.0839
-8.750 -0.1948 0.09241 0.08792 -0.0672 0.9390 0.0842
-8.500 -0.1789 0.08701 0.08251 -0.0730 0.9250 0.0844
-8.000 -0.1590 0.06775 0.06300 -0.0878 0.8962 0.0533
-7.750 -0.1441 0.06315 0.05830 -0.0925 0.8796 0.0529
-7.500 -0.1319 0.05896 0.05399 -0.0961 0.8626 0.0523
-7.250 -0.1239 0.05463 0.04948 -0.0991 0.8454 0.0514
-7.000 -0.1187 0.05002 0.04462 -0.1015 0.8290 0.0504
-6.750 -0.1138 0.04547 0.03973 -0.1030 0.8136 0.0495
-6.500 -0.1063 0.04131 0.03513 -0.1035 0.7994 0.0488
-6.250 -0.0944 0.03782 0.03117 -0.1035 0.7865 0.0483
-6.000 -0.0770 0.03533 0.02828 -0.1033 0.7746 0.0487
-5.750 -0.0588 0.03333 0.02592 -0.1026 0.7616 0.0496
-5.500 -0.0394 0.03143 0.02363 -0.1019 0.7492 0.0502
-5.250 -0.0178 0.02963 0.02143 -0.1013 0.7382 0.0503
-5.000 0.0045 0.02807 0.01949 -0.1005 0.7272 0.0504
-4.750 0.0276 0.02672 0.01782 -0.0998 0.7164 0.0506
-4.250 0.0768 0.02451 0.01503 -0.0984 0.6963 0.0513
-4.000 0.1024 0.02361 0.01388 -0.0979 0.6872 0.0518
-3.750 0.1276 0.02288 0.01292 -0.0971 0.6768 0.0528
-3.500 0.1523 0.02217 0.01209 -0.0964 0.6657 0.0541
-3.250 0.1774 0.02156 0.01140 -0.0958 0.6553 0.0556
-3.000 0.2017 0.02103 0.01080 -0.0949 0.6440 0.0567
-2.750 0.2266 0.02053 0.01020 -0.0942 0.6346 0.0578
-2.500 0.2515 0.02010 0.00969 -0.0934 0.6264 0.0590
-2.250 0.2763 0.01974 0.00924 -0.0927 0.6187 0.0605
-2.000 0.3011 0.01944 0.00884 -0.0919 0.6108 0.0621
-1.750 0.3260 0.01912 0.00847 -0.0913 0.6039 0.0648
-1.500 0.3509 0.01892 0.00822 -0.0906 0.5962 0.0696
-1.000 0.4014 0.01848 0.00771 -0.0894 0.5822 0.0867
-0.750 0.4266 0.01809 0.00746 -0.0888 0.5756 0.1292
-0.500 0.4505 0.01737 0.00742 -0.0884 0.5689 0.3156
-0.250 0.4722 0.01680 0.00755 -0.0872 0.5617 0.5321
0.000 0.5413 0.01584 0.00759 -0.0939 0.5532 0.9707
0.250 0.5780 0.01601 0.00756 -0.0958 0.5452 1.0000
0.500 0.6021 0.01618 0.00749 -0.0950 0.5393 1.0000
0.750 0.6239 0.01638 0.00759 -0.0939 0.5315 1.0000
1.000 0.6474 0.01657 0.00760 -0.0930 0.5246 1.0000
1.250 0.6705 0.01678 0.00767 -0.0921 0.5175 1.0000
1.500 0.6934 0.01699 0.00776 -0.0911 0.5098 1.0000
1.750 0.7176 0.01720 0.00781 -0.0903 0.5035 1.0000
2.000 0.7397 0.01744 0.00800 -0.0893 0.4955 1.0000
2.250 0.7637 0.01765 0.00807 -0.0885 0.4887 1.0000
2.500 0.7859 0.01789 0.00827 -0.0875 0.4806 1.0000
2.750 0.8091 0.01811 0.00839 -0.0866 0.4731 1.0000
3.000 0.8317 0.01836 0.00858 -0.0856 0.4653 1.0000
3.250 0.8543 0.01860 0.00876 -0.0847 0.4576 1.0000
3.500 0.8773 0.01886 0.00895 -0.0838 0.4508 1.0000
3.750 0.8994 0.01913 0.00919 -0.0828 0.4429 1.0000
4.000 0.9225 0.01938 0.00935 -0.0820 0.4364 1.0000
4.250 0.9439 0.01968 0.00966 -0.0809 0.4283 1.0000
4.500 0.9669 0.01994 0.00981 -0.0801 0.4223 1.0000
4.750 0.9881 0.02029 0.01019 -0.0790 0.4148 1.0000
5.000 1.0104 0.02059 0.01044 -0.0781 0.4089 1.0000
5.250 1.0322 0.02094 0.01075 -0.0772 0.4028 1.0000
5.500 1.0533 0.02130 0.01112 -0.0762 0.3964 1.0000
5.750 1.0757 0.02161 0.01135 -0.0753 0.3914 1.0000
6.000 1.0960 0.02205 0.01182 -0.0742 0.3854 1.0000
6.250 1.1169 0.02245 0.01222 -0.0732 0.3800 1.0000
6.500 1.1394 0.02280 0.01249 -0.0724 0.3756 1.0000
6.750 1.1584 0.02331 0.01306 -0.0712 0.3700 1.0000
7.000 1.1783 0.02376 0.01354 -0.0701 0.3649 1.0000
7.250 1.2001 0.02417 0.01389 -0.0693 0.3607 1.0000
7.500 1.2187 0.02471 0.01448 -0.0680 0.3558 1.0000
7.750 1.2366 0.02524 0.01507 -0.0667 0.3507 1.0000
8.000 1.2568 0.02571 0.01553 -0.0657 0.3463 1.0000
8.250 1.2766 0.02624 0.01605 -0.0647 0.3420 1.0000
8.500 1.2908 0.02688 0.01680 -0.0629 0.3369 1.0000
8.750 1.3077 0.02743 0.01739 -0.0615 0.3322 1.0000
9.000 1.3292 0.02790 0.01781 -0.0608 0.3281 1.0000
9.250 1.3386 0.02864 0.01868 -0.0583 0.3235 1.0000
9.500 1.3496 0.02933 0.01947 -0.0562 0.3187 1.0000
9.750 1.3656 0.02992 0.02009 -0.0547 0.3144 1.0000
10.000 1.3839 0.03054 0.02071 -0.0537 0.3105 1.0000
10.250 1.3881 0.03152 0.02187 -0.0510 0.3060 1.0000
10.500 1.3978 0.03238 0.02283 -0.0490 0.3016 1.0000
10.750 1.4134 0.03306 0.02353 -0.0478 0.2976 1.0000
11.000 1.4243 0.03394 0.02449 -0.0462 0.2934 1.0000
11.250 1.4238 0.03530 0.02604 -0.0436 0.2887 1.0000
11.500 1.4294 0.03636 0.02717 -0.0417 0.2835 1.0000
11.750 1.4395 0.03720 0.02801 -0.0403 0.2783 1.0000
12.000 1.4306 0.03926 0.03029 -0.0379 0.2728 1.0000
12.250 1.4315 0.04076 0.03188 -0.0363 0.2670 1.0000
12.500 1.4345 0.04226 0.03343 -0.0349 0.2619 1.0000
12.750 1.4234 0.04503 0.03642 -0.0335 0.2562 1.0000
13.000 1.4233 0.04700 0.03846 -0.0325 0.2510 1.0000
13.250 1.4212 0.04930 0.04085 -0.0317 0.2461 1.0000
13.500 1.4072 0.05301 0.04477 -0.0312 0.2408 1.0000
13.750 1.4041 0.05563 0.04746 -0.0308 0.2356 1.0000
14.000 1.3933 0.05933 0.05129 -0.0308 0.2303 1.0000
14.250 1.3737 0.06439 0.05653 -0.0313 0.2250 1.0000
14.500 1.3769 0.06653 0.05868 -0.0313 0.2191 1.0000
14.750 1.3426 0.07414 0.06652 -0.0330 0.2140 1.0000
15.000 1.3237 0.07984 0.07236 -0.0343 0.2086 1.0000
15.250 1.3202 0.08333 0.07589 -0.0350 0.2034 1.0000
15.500 1.2695 0.09456 0.08733 -0.0385 0.1982 1.0000
15.750 1.2761 0.09666 0.08948 -0.0389 0.1928 1.0000
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Polar data table (+)
Polar graphs
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