GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 200,000 Max Cl/Cd: 69.77 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe425-il-200000.txt Download as CSV file: xf-goe425-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2435 0.10201 0.09852 -0.0530 0.8911 0.0738
-10.000 -0.2738 0.09459 0.09106 -0.0622 0.8664 0.0775
-9.750 -0.2560 0.09321 0.08955 -0.0586 0.8448 0.0783
-9.500 -0.2434 0.09146 0.08769 -0.0571 0.8275 0.0797
-9.250 -0.2359 0.08907 0.08521 -0.0573 0.8134 0.0819
-9.000 -0.3256 0.07491 0.07081 -0.0854 0.8031 0.0875
-8.750 -0.2596 0.07735 0.07345 -0.0696 0.7920 0.0889
-8.500 -0.2407 0.07676 0.07275 -0.0662 0.7817 0.0904
-8.250 -0.2311 0.07438 0.07035 -0.0668 0.7715 0.0929
-8.000 -0.2965 0.06074 0.05618 -0.0893 0.7652 0.1001
-7.750 -0.2683 0.05842 0.05405 -0.0873 0.7563 0.1015
-7.500 -0.2496 0.05679 0.05241 -0.0863 0.7479 0.1032
-7.250 -0.2371 0.05432 0.04985 -0.0870 0.7399 0.1064
-7.000 -0.2441 0.04881 0.04380 -0.0913 0.7329 0.1147
-6.750 -0.2235 0.04670 0.04170 -0.0908 0.7260 0.1167
-6.500 -0.2056 0.04462 0.03955 -0.0909 0.7179 0.1201
-6.250 -0.2069 0.03239 0.02558 -0.0914 0.7139 0.0786
-6.000 -0.1862 0.02822 0.02058 -0.0899 0.7087 0.0668
-5.750 -0.1627 0.02612 0.01833 -0.0896 0.7014 0.0653
-5.500 -0.1382 0.02437 0.01629 -0.0890 0.6954 0.0639
-5.250 -0.1127 0.02297 0.01458 -0.0885 0.6899 0.0630
-5.000 -0.0867 0.02182 0.01326 -0.0881 0.6831 0.0627
-4.750 -0.0602 0.02099 0.01227 -0.0878 0.6774 0.0633
-4.500 -0.0335 0.02030 0.01144 -0.0874 0.6724 0.0642
-4.250 -0.0069 0.01960 0.01069 -0.0871 0.6664 0.0648
-4.000 0.0197 0.01894 0.00997 -0.0868 0.6613 0.0653
-3.750 0.0465 0.01840 0.00933 -0.0864 0.6571 0.0659
-3.500 0.0724 0.01793 0.00885 -0.0860 0.6519 0.0667
-3.250 0.0984 0.01749 0.00839 -0.0856 0.6466 0.0677
-3.000 0.1240 0.01698 0.00788 -0.0852 0.6423 0.0695
-2.750 0.1506 0.01673 0.00758 -0.0850 0.6388 0.0726
-2.500 0.1768 0.01651 0.00740 -0.0847 0.6339 0.0762
-2.250 0.2032 0.01627 0.00719 -0.0845 0.6293 0.0808
-2.000 0.2305 0.01608 0.00698 -0.0843 0.6253 0.0891
-1.750 0.2579 0.01586 0.00674 -0.0841 0.6220 0.1140
-1.500 0.2795 0.01487 0.00659 -0.0836 0.6180 0.2989
-1.250 0.3013 0.01439 0.00681 -0.0827 0.6136 0.4969
-1.000 0.3271 0.01434 0.00687 -0.0821 0.6097 0.5571
-0.750 0.3535 0.01431 0.00690 -0.0816 0.6064 0.6019
-0.500 0.3798 0.01436 0.00699 -0.0811 0.6032 0.6365
-0.250 0.4047 0.01437 0.00714 -0.0805 0.5988 0.6720
0.000 0.4300 0.01431 0.00720 -0.0798 0.5948 0.7085
0.250 0.4553 0.01419 0.00722 -0.0789 0.5914 0.7542
0.500 0.4820 0.01403 0.00726 -0.0781 0.5885 0.8268
0.750 0.5372 0.01405 0.00746 -0.0833 0.5841 0.9320
1.000 0.5964 0.01418 0.00754 -0.0900 0.5793 0.9941
1.250 0.6292 0.01430 0.00754 -0.0913 0.5756 1.0000
1.500 0.6553 0.01444 0.00753 -0.0911 0.5726 1.0000
1.750 0.6809 0.01468 0.00767 -0.0909 0.5694 1.0000
2.000 0.7040 0.01493 0.00794 -0.0902 0.5652 1.0000
2.250 0.7288 0.01513 0.00810 -0.0897 0.5613 1.0000
2.500 0.7549 0.01529 0.00818 -0.0895 0.5579 1.0000
2.750 0.7822 0.01548 0.00826 -0.0894 0.5550 1.0000
3.000 0.8069 0.01579 0.00856 -0.0890 0.5516 1.0000
3.250 0.8303 0.01608 0.00889 -0.0884 0.5474 1.0000
3.500 0.8557 0.01629 0.00909 -0.0880 0.5435 1.0000
3.750 0.8826 0.01646 0.00919 -0.0879 0.5402 1.0000
4.000 0.9109 0.01670 0.00933 -0.0880 0.5373 1.0000
4.250 0.9335 0.01708 0.00980 -0.0873 0.5334 1.0000
4.500 0.9573 0.01740 0.01017 -0.0868 0.5292 1.0000
4.750 0.9832 0.01763 0.01039 -0.0865 0.5255 1.0000
5.000 1.0110 0.01781 0.01052 -0.0865 0.5224 1.0000
5.250 1.0382 0.01813 0.01079 -0.0865 0.5191 1.0000
5.500 1.0590 0.01852 0.01131 -0.0856 0.5141 1.0000
5.750 1.0840 0.01875 0.01157 -0.0852 0.5097 1.0000
6.000 1.1117 0.01889 0.01167 -0.0852 0.5061 1.0000
6.250 1.1408 0.01913 0.01184 -0.0855 0.5028 1.0000
6.500 1.1595 0.01953 0.01242 -0.0843 0.4972 1.0000
6.750 1.1845 0.01968 0.01260 -0.0839 0.4923 1.0000
7.000 1.2131 0.01977 0.01264 -0.0840 0.4886 1.0000
7.250 1.2391 0.02011 0.01300 -0.0839 0.4850 1.0000
7.500 1.2581 0.02054 0.01359 -0.0827 0.4796 1.0000
7.750 1.2832 0.02067 0.01375 -0.0823 0.4750 1.0000
8.000 1.3146 0.02054 0.01352 -0.0828 0.4705 1.0000
8.250 1.3313 0.02085 0.01401 -0.0812 0.4637 1.0000
8.500 1.3559 0.02086 0.01405 -0.0807 0.4581 1.0000
8.750 1.3859 0.02085 0.01397 -0.0811 0.4541 1.0000
9.000 1.4018 0.02127 0.01459 -0.0794 0.4480 1.0000
9.250 1.4249 0.02126 0.01463 -0.0787 0.4418 1.0000
9.500 1.4519 0.02122 0.01455 -0.0786 0.4366 1.0000
9.750 1.4662 0.02157 0.01510 -0.0767 0.4296 1.0000
10.000 1.4902 0.02155 0.01509 -0.0761 0.4238 1.0000
10.250 1.5081 0.02185 0.01550 -0.0747 0.4178 1.0000
10.500 1.5249 0.02208 0.01585 -0.0732 0.4109 1.0000
10.750 1.5461 0.02216 0.01594 -0.0722 0.4046 1.0000
11.000 1.5554 0.02259 0.01653 -0.0697 0.3962 1.0000
11.250 1.5693 0.02278 0.01675 -0.0676 0.3880 1.0000
11.500 1.5736 0.02328 0.01736 -0.0644 0.3785 1.0000
11.750 1.5780 0.02395 0.01810 -0.0614 0.3681 1.0000
12.000 1.5819 0.02474 0.01891 -0.0588 0.3564 1.0000
12.250 1.5825 0.02588 0.02006 -0.0562 0.3431 1.0000
12.500 1.5796 0.02748 0.02169 -0.0537 0.3283 1.0000
12.750 1.5737 0.02959 0.02383 -0.0516 0.3116 1.0000
13.000 1.5646 0.03224 0.02650 -0.0499 0.2924 1.0000
13.250 1.5509 0.03551 0.02972 -0.0482 0.2708 1.0000
13.500 1.5329 0.03937 0.03350 -0.0468 0.2469 1.0000
13.750 1.5103 0.04380 0.03782 -0.0454 0.2246 1.0000
14.000 1.4886 0.04836 0.04228 -0.0443 0.2054 1.0000
14.250 1.4686 0.05296 0.04678 -0.0435 0.1907 1.0000
14.500 1.4521 0.05732 0.05104 -0.0429 0.1792 1.0000
14.750 1.4397 0.06134 0.05499 -0.0424 0.1690 1.0000
15.000 1.4325 0.06487 0.05852 -0.0420 0.1597 1.0000
15.250 1.4252 0.06834 0.06189 -0.0416 0.1520 1.0000
15.500 1.4227 0.07153 0.06516 -0.0416 0.1443 1.0000
15.750 1.4199 0.07455 0.06811 -0.0412 0.1380 1.0000
16.000 1.4197 0.07758 0.07127 -0.0413 0.1318 1.0000
16.250 1.4179 0.08064 0.07429 -0.0413 0.1263 1.0000
16.500 1.4183 0.08362 0.07737 -0.0415 0.1209 1.0000
16.750 1.4173 0.08681 0.08061 -0.0418 0.1157 1.0000
17.000 1.4160 0.08994 0.08374 -0.0420 0.1109 1.0000
17.250 1.4156 0.09318 0.08710 -0.0425 0.1058 1.0000
17.500 1.4125 0.09669 0.09060 -0.0430 0.1011 1.0000
17.750 1.4116 0.10000 0.09402 -0.0436 0.0962 1.0000
18.000 1.4079 0.10373 0.09778 -0.0444 0.0912 1.0000
18.250 1.4047 0.10736 0.10146 -0.0451 0.0861 1.0000
18.500 1.3993 0.11139 0.10553 -0.0461 0.0806 1.0000
18.750 1.3935 0.11551 0.10969 -0.0472 0.0746 1.0000
19.000 1.3859 0.11987 0.11400 -0.0485 0.0686 1.0000
19.250 1.3784 0.12453 0.11878 -0.0500 0.0619 1.0000
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Polar data table (+)
Polar graphs
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