GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 100,000 Max Cl/Cd: 47.11 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe573-il-100000-n5.txt Download as CSV file: xf-goe573-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 573 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2128 0.14021 0.13553 -0.0431 1.0000 0.0396
-11.750 -0.2167 0.13850 0.13390 -0.0443 1.0000 0.0398
-11.500 -0.2236 0.13714 0.13262 -0.0457 1.0000 0.0400
-11.250 -0.2259 0.13490 0.13047 -0.0462 1.0000 0.0401
-11.000 -0.1965 0.12757 0.12314 -0.0444 0.9985 0.0415
-10.750 -0.1751 0.12285 0.11840 -0.0485 0.9906 0.0426
-10.500 -0.1609 0.11893 0.11450 -0.0514 0.9746 0.0438
-10.250 -0.1520 0.11553 0.11113 -0.0532 0.9439 0.0449
-10.000 -0.1356 0.11142 0.10699 -0.0581 0.9235 0.0470
-9.750 -0.1212 0.10770 0.10322 -0.0666 0.9072 0.0493
-9.500 -0.1048 0.10377 0.09922 -0.0775 0.8909 0.0499
-9.250 -0.0674 0.09661 0.09196 -0.0811 0.8782 0.0516
-9.000 -0.0322 0.09161 0.08680 -0.0876 0.8593 0.0536
-8.750 -0.0055 0.08730 0.08233 -0.0943 0.8371 0.0560
-8.500 0.0111 0.08368 0.07858 -0.0999 0.8141 0.0588
-8.250 0.0079 0.08112 0.07594 -0.1070 0.7905 0.0612
-7.750 0.0042 0.07494 0.06955 -0.1134 0.7550 0.0622
-7.500 0.0327 0.07133 0.06588 -0.1101 0.7398 0.0649
-7.250 0.0398 0.06877 0.06324 -0.1106 0.7254 0.0665
-7.000 0.0451 0.06614 0.06053 -0.1115 0.7126 0.0682
-6.750 0.0502 0.06347 0.05776 -0.1126 0.7012 0.0700
-6.500 0.0460 0.06142 0.05535 -0.1158 0.6915 0.0749
-6.000 0.0667 0.05519 0.04906 -0.1139 0.6721 0.0783
-5.500 0.0847 0.04773 0.04112 -0.1127 0.6561 0.0570
-5.250 0.0924 0.04420 0.03727 -0.1113 0.6480 0.0534
-5.000 0.1057 0.04207 0.03489 -0.1100 0.6405 0.0544
-4.750 0.1185 0.03990 0.03247 -0.1083 0.6322 0.0551
-4.500 0.1322 0.03733 0.02950 -0.1065 0.6259 0.0539
-4.250 0.1452 0.03487 0.02666 -0.1041 0.6182 0.0528
-4.000 0.1615 0.03280 0.02417 -0.1021 0.6117 0.0524
-3.750 0.1796 0.03158 0.02273 -0.1006 0.6047 0.0538
-3.500 0.1986 0.03034 0.02121 -0.0991 0.5981 0.0554
-3.250 0.2189 0.02893 0.01943 -0.0976 0.5923 0.0557
-3.000 0.2390 0.02763 0.01782 -0.0960 0.5855 0.0558
-2.750 0.2615 0.02647 0.01630 -0.0948 0.5798 0.0561
-2.500 0.2842 0.02549 0.01503 -0.0936 0.5736 0.0566
-2.250 0.3076 0.02477 0.01404 -0.0926 0.5674 0.0586
-2.000 0.3335 0.02408 0.01303 -0.0920 0.5625 0.0603
-1.750 0.3577 0.02343 0.01220 -0.0911 0.5566 0.0609
-1.500 0.3834 0.02285 0.01144 -0.0906 0.5514 0.0615
-1.250 0.4105 0.02223 0.01067 -0.0904 0.5472 0.0625
-1.000 0.4350 0.02172 0.01015 -0.0898 0.5422 0.0640
-0.750 0.4591 0.02137 0.00980 -0.0891 0.5373 0.0660
-0.500 0.4839 0.02113 0.00950 -0.0886 0.5331 0.0697
-0.250 0.5087 0.02093 0.00919 -0.0879 0.5290 0.0735
0.000 0.5312 0.02074 0.00899 -0.0869 0.5243 0.0763
0.250 0.5560 0.02060 0.00880 -0.0864 0.5202 0.0809
0.500 0.5843 0.02053 0.00861 -0.0865 0.5168 0.0886
0.750 0.6133 0.02048 0.00856 -0.0869 0.5136 0.1079
1.250 0.8115 0.01911 0.00895 -0.1178 0.5030 1.0000
1.500 0.8351 0.01933 0.00899 -0.1170 0.5002 1.0000
1.750 0.8558 0.01962 0.00922 -0.1158 0.4968 1.0000
2.000 0.8760 0.01992 0.00948 -0.1145 0.4932 1.0000
2.250 0.8975 0.02021 0.00971 -0.1134 0.4902 1.0000
2.500 0.9198 0.02049 0.00990 -0.1126 0.4875 1.0000
2.750 0.9433 0.02076 0.01008 -0.1119 0.4852 1.0000
3.000 0.9650 0.02108 0.01035 -0.1109 0.4826 1.0000
3.250 0.9827 0.02147 0.01077 -0.1092 0.4792 1.0000
3.500 1.0021 0.02183 0.01114 -0.1078 0.4761 1.0000
3.750 1.0230 0.02217 0.01145 -0.1067 0.4734 1.0000
4.000 1.0452 0.02249 0.01174 -0.1059 0.4711 1.0000
4.250 1.0692 0.02280 0.01198 -0.1053 0.4690 1.0000
4.500 1.0867 0.02324 0.01248 -0.1037 0.4661 1.0000
4.750 1.1020 0.02374 0.01305 -0.1017 0.4630 1.0000
5.000 1.1195 0.02418 0.01355 -0.1000 0.4600 1.0000
5.250 1.1391 0.02456 0.01395 -0.0987 0.4574 1.0000
5.500 1.1612 0.02490 0.01427 -0.0979 0.4550 1.0000
5.750 1.1866 0.02519 0.01452 -0.0977 0.4527 1.0000
6.000 1.1951 0.02584 0.01533 -0.0946 0.4491 1.0000
6.250 1.2072 0.02639 0.01599 -0.0920 0.4456 1.0000
6.500 1.2237 0.02679 0.01643 -0.0902 0.4422 1.0000
6.750 1.2457 0.02706 0.01671 -0.0894 0.4392 1.0000
7.000 1.2708 0.02731 0.01693 -0.0892 0.4365 1.0000
7.250 1.2713 0.02814 0.01796 -0.0847 0.4325 1.0000
7.500 1.2800 0.02879 0.01873 -0.0818 0.4291 1.0000
7.750 1.2945 0.02927 0.01929 -0.0798 0.4260 1.0000
8.000 1.3151 0.02963 0.01970 -0.0788 0.4235 1.0000
8.250 1.3417 0.02990 0.01998 -0.0789 0.4214 1.0000
8.500 1.3332 0.03103 0.02132 -0.0733 0.4176 1.0000
8.750 1.3278 0.03198 0.02241 -0.0682 0.4139 1.0000
9.000 1.3341 0.03264 0.02316 -0.0650 0.4108 1.0000
9.250 1.3531 0.03296 0.02356 -0.0638 0.4080 1.0000
9.500 1.3840 0.03310 0.02374 -0.0645 0.4057 1.0000
9.750 1.3471 0.03511 0.02596 -0.0554 0.4013 1.0000
10.000 1.3300 0.03691 0.02793 -0.0501 0.3971 1.0000
10.250 1.3380 0.03781 0.02892 -0.0479 0.3939 1.0000
10.500 1.3636 0.03789 0.02910 -0.0477 0.3915 1.0000
10.750 1.2744 0.04471 0.03611 -0.0382 0.3833 1.0000
11.000 1.2645 0.04734 0.03884 -0.0359 0.3785 1.0000
11.250 1.3025 0.04608 0.03769 -0.0360 0.3765 1.0000
11.500 1.1587 0.06243 0.05408 -0.0316 0.3578 1.0000
11.750 1.2051 0.05957 0.05133 -0.0310 0.3590 1.0000
12.750 1.0740 0.08720 0.07920 -0.0303 0.3178 1.0000
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Polar data table (+)
Polar graphs
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