GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 424 AIRFOIL (goe424-il) Reynolds number: 500,000 Max Cl/Cd: 96.38 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe424-il-500000.txt Download as CSV file: xf-goe424-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 424 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.4182 0.08830 0.08583 -0.0807 0.9965 0.0292
-13.750 -0.4533 0.07599 0.07340 -0.0908 0.9945 0.0289
-13.500 -0.4920 0.06454 0.06172 -0.1015 0.9915 0.0286
-13.250 -0.5303 0.05491 0.05178 -0.1103 0.9865 0.0286
-13.000 -0.5698 0.04619 0.04257 -0.1172 0.9819 0.0289
-12.750 -0.6064 0.04039 0.03623 -0.1177 0.9713 0.0293
-12.500 -0.6006 0.03812 0.03387 -0.1174 0.9635 0.0296
-12.250 -0.5883 0.03711 0.03283 -0.1165 0.9549 0.0299
-12.000 -0.5751 0.03672 0.03245 -0.1149 0.9440 0.0302
-11.750 -0.5641 0.03615 0.03186 -0.1131 0.9334 0.0305
-11.500 -0.5548 0.03516 0.03077 -0.1111 0.9217 0.0309
-11.250 -0.5476 0.03392 0.02938 -0.1090 0.9073 0.0315
-11.000 -0.5421 0.03226 0.02746 -0.1065 0.8914 0.0323
-10.750 -0.5400 0.03020 0.02494 -0.1034 0.8734 0.0334
-10.500 -0.5309 0.02823 0.02261 -0.1013 0.8538 0.0341
-10.250 -0.5114 0.02735 0.02164 -0.1004 0.8316 0.0345
-10.000 -0.4900 0.02692 0.02113 -0.0996 0.8071 0.0350
-9.750 -0.4706 0.02635 0.02040 -0.0985 0.7812 0.0356
-9.500 -0.4523 0.02567 0.01948 -0.0972 0.7519 0.0364
-9.250 -0.4347 0.02491 0.01842 -0.0957 0.7206 0.0375
-9.000 -0.4180 0.02435 0.01748 -0.0939 0.6921 0.0384
-8.750 -0.3988 0.02313 0.01599 -0.0928 0.6698 0.0391
-8.500 -0.3755 0.02230 0.01506 -0.0923 0.6532 0.0398
-8.250 -0.3520 0.02181 0.01451 -0.0919 0.6405 0.0405
-8.000 -0.3288 0.02137 0.01398 -0.0913 0.6300 0.0414
-7.750 -0.3052 0.02088 0.01336 -0.0907 0.6217 0.0425
-7.500 -0.2814 0.02037 0.01270 -0.0900 0.6141 0.0434
-7.250 -0.2578 0.02005 0.01220 -0.0893 0.6076 0.0441
-7.000 -0.2321 0.01909 0.01118 -0.0891 0.6019 0.0449
-6.750 -0.2067 0.01836 0.01046 -0.0890 0.5963 0.0459
-6.500 -0.1820 0.01798 0.01003 -0.0886 0.5910 0.0469
-6.250 -0.1565 0.01752 0.00956 -0.0883 0.5866 0.0478
-6.000 -0.1313 0.01710 0.00910 -0.0879 0.5821 0.0487
-5.750 -0.1063 0.01675 0.00869 -0.0874 0.5781 0.0496
-5.500 -0.0810 0.01659 0.00842 -0.0870 0.5741 0.0504
-5.250 -0.0572 0.01598 0.00780 -0.0864 0.5708 0.0515
-5.000 -0.0341 0.01542 0.00728 -0.0858 0.5677 0.0525
-4.750 -0.0103 0.01505 0.00692 -0.0852 0.5645 0.0535
-4.500 0.0139 0.01475 0.00660 -0.0846 0.5613 0.0546
-4.250 0.0382 0.01452 0.00632 -0.0840 0.5582 0.0558
-4.000 0.0635 0.01439 0.00611 -0.0837 0.5547 0.0571
-3.750 0.0891 0.01420 0.00592 -0.0833 0.5523 0.0580
-3.500 0.1115 0.01374 0.00545 -0.0824 0.5497 0.0596
-3.250 0.1360 0.01347 0.00518 -0.0819 0.5472 0.0612
-3.000 0.1615 0.01328 0.00497 -0.0816 0.5446 0.0630
-2.750 0.1876 0.01315 0.00480 -0.0813 0.5422 0.0651
-2.500 0.2138 0.01304 0.00463 -0.0811 0.5397 0.0674
-2.250 0.2405 0.01297 0.00452 -0.0810 0.5368 0.0710
-2.000 0.2667 0.01283 0.00439 -0.0808 0.5348 0.0752
-1.750 0.2913 0.01253 0.00425 -0.0803 0.5327 0.1131
-1.500 0.3067 0.01139 0.00404 -0.0787 0.5307 0.3655
-1.250 0.3301 0.01106 0.00403 -0.0781 0.5285 0.4561
-1.000 0.3547 0.01088 0.00404 -0.0776 0.5264 0.5184
-0.750 0.3803 0.01078 0.00408 -0.0773 0.5242 0.5661
-0.500 0.4066 0.01075 0.00414 -0.0771 0.5219 0.6071
-0.250 0.4341 0.01083 0.00427 -0.0771 0.5193 0.6423
0.000 0.4604 0.01080 0.00433 -0.0769 0.5178 0.6684
0.250 0.4868 0.01077 0.00439 -0.0767 0.5160 0.6938
0.500 0.5130 0.01075 0.00447 -0.0764 0.5138 0.7205
0.750 0.5394 0.01075 0.00454 -0.0762 0.5116 0.7475
1.000 0.5658 0.01076 0.00463 -0.0759 0.5095 0.7732
1.250 0.5922 0.01078 0.00472 -0.0756 0.5076 0.8027
1.500 0.6187 0.01083 0.00483 -0.0754 0.5055 0.8282
1.750 0.6461 0.01097 0.00498 -0.0753 0.5032 0.8517
2.000 0.6726 0.01112 0.00517 -0.0750 0.5011 0.8765
2.250 0.6975 0.01117 0.00530 -0.0743 0.4994 0.8988
2.500 0.7232 0.01125 0.00543 -0.0739 0.4972 0.9163
2.750 0.7507 0.01135 0.00555 -0.0738 0.4949 0.9308
3.000 0.7807 0.01147 0.00568 -0.0743 0.4926 0.9438
3.250 0.8125 0.01161 0.00580 -0.0753 0.4902 0.9552
3.500 0.8443 0.01176 0.00591 -0.0763 0.4877 0.9659
3.750 0.8833 0.01201 0.00610 -0.0789 0.4841 0.9703
4.000 0.9189 0.01205 0.00619 -0.0808 0.4807 0.9763
4.250 0.9553 0.01214 0.00628 -0.0830 0.4773 0.9815
4.500 0.9962 0.01226 0.00638 -0.0861 0.4744 0.9844
4.750 1.0356 0.01238 0.00648 -0.0889 0.4717 0.9883
5.000 1.0739 0.01259 0.00664 -0.0915 0.4690 0.9923
5.250 1.1158 0.01276 0.00682 -0.0949 0.4664 0.9952
5.500 1.1586 0.01286 0.00698 -0.0986 0.4637 0.9991
5.750 1.1808 0.01293 0.00708 -0.0980 0.4608 1.0000
6.000 1.1950 0.01298 0.00713 -0.0956 0.4581 1.0000
6.250 1.2096 0.01303 0.00718 -0.0933 0.4554 1.0000
6.500 1.2271 0.01315 0.00727 -0.0916 0.4526 1.0000
6.750 1.2436 0.01328 0.00742 -0.0897 0.4499 1.0000
7.000 1.2566 0.01335 0.00754 -0.0870 0.4471 1.0000
7.250 1.2713 0.01342 0.00766 -0.0848 0.4440 1.0000
7.500 1.2869 0.01350 0.00775 -0.0826 0.4407 1.0000
7.750 1.3041 0.01361 0.00784 -0.0809 0.4374 1.0000
8.000 1.3215 0.01377 0.00799 -0.0792 0.4337 1.0000
8.250 1.3334 0.01386 0.00817 -0.0764 0.4296 1.0000
8.500 1.3483 0.01399 0.00833 -0.0744 0.4249 1.0000
8.750 1.3656 0.01417 0.00849 -0.0728 0.4204 1.0000
9.000 1.3830 0.01439 0.00876 -0.0714 0.4160 1.0000
9.250 1.4004 0.01461 0.00905 -0.0700 0.4110 1.0000
9.500 1.4175 0.01488 0.00932 -0.0686 0.4060 1.0000
9.750 1.4342 0.01520 0.00967 -0.0672 0.4007 1.0000
10.000 1.4508 0.01552 0.01004 -0.0658 0.3939 1.0000
10.500 1.4811 0.01637 0.01094 -0.0629 0.3798 1.0000
10.750 1.4925 0.01699 0.01153 -0.0610 0.3719 1.0000
11.000 1.5064 0.01757 0.01216 -0.0596 0.3623 1.0000
11.250 1.5163 0.01836 0.01294 -0.0577 0.3525 1.0000
11.500 1.5234 0.01935 0.01391 -0.0557 0.3418 1.0000
11.750 1.5322 0.02035 0.01492 -0.0539 0.3308 1.0000
12.000 1.5380 0.02156 0.01613 -0.0520 0.3206 1.0000
12.250 1.5395 0.02311 0.01764 -0.0499 0.3102 1.0000
12.500 1.5446 0.02455 0.01910 -0.0482 0.2998 1.0000
12.750 1.5462 0.02628 0.02084 -0.0465 0.2904 1.0000
13.000 1.5453 0.02830 0.02285 -0.0447 0.2814 1.0000
13.250 1.5484 0.03015 0.02474 -0.0435 0.2735 1.0000
13.500 1.5452 0.03256 0.02715 -0.0420 0.2658 1.0000
13.750 1.5472 0.03467 0.02930 -0.0410 0.2589 1.0000
14.000 1.5439 0.03729 0.03195 -0.0398 0.2520 1.0000
14.250 1.5430 0.03978 0.03447 -0.0390 0.2458 1.0000
14.500 1.5411 0.04241 0.03714 -0.0382 0.2393 1.0000
14.750 1.5353 0.04544 0.04018 -0.0373 0.2334 1.0000
15.000 1.5369 0.04785 0.04266 -0.0368 0.2277 1.0000
15.250 1.5319 0.05089 0.04571 -0.0361 0.2220 1.0000
15.500 1.5296 0.05369 0.04855 -0.0356 0.2167 1.0000
15.750 1.5287 0.05639 0.05130 -0.0352 0.2110 1.0000
16.000 1.5221 0.05967 0.05457 -0.0347 0.2053 1.0000
16.250 1.5225 0.06233 0.05731 -0.0345 0.1998 1.0000
16.500 1.5191 0.06536 0.06036 -0.0342 0.1939 1.0000
16.750 1.5151 0.06848 0.06350 -0.0340 0.1888 1.0000
17.000 1.5163 0.07112 0.06621 -0.0339 0.1832 1.0000
17.250 1.5106 0.07451 0.06960 -0.0338 0.1773 1.0000
17.500 1.5093 0.07744 0.07259 -0.0338 0.1711 1.0000
17.750 1.5036 0.08090 0.07606 -0.0338 0.1641 1.0000
18.000 1.5001 0.08416 0.07935 -0.0339 0.1572 1.0000
18.250 1.4917 0.08801 0.08319 -0.0341 0.1494 1.0000
18.500 1.4865 0.09153 0.08674 -0.0344 0.1414 1.0000
18.750 1.4779 0.09545 0.09065 -0.0347 0.1337 1.0000
19.000 1.4680 0.09960 0.09480 -0.0351 0.1257 1.0000
19.250 1.4593 0.10364 0.09884 -0.0356 0.1177 1.0000
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Polar data table (+)
Polar graphs
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