GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.04 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe438-il-1000000-n5.txt Download as CSV file: xf-goe438-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5489 0.12140 0.11945 -0.0297 1.0000 0.0129
-14.250 -0.5465 0.11794 0.11601 -0.0312 1.0000 0.0134
-13.250 -1.0161 0.02602 0.02253 -0.0816 0.9954 0.0110
-13.000 -0.9971 0.02361 0.01989 -0.0823 0.9928 0.0116
-12.750 -0.9749 0.02203 0.01814 -0.0827 0.9899 0.0120
-12.500 -0.9517 0.02037 0.01631 -0.0833 0.9873 0.0128
-12.250 -0.9266 0.01885 0.01464 -0.0841 0.9853 0.0139
-11.750 -0.8772 0.01654 0.01210 -0.0846 0.9794 0.0172
-11.500 -0.8507 0.01557 0.01107 -0.0850 0.9767 0.0206
-11.250 -0.8209 0.01504 0.01057 -0.0857 0.9749 0.0248
-11.000 -0.7886 0.01475 0.01027 -0.0868 0.9734 0.0272
-10.750 -0.7589 0.01451 0.01000 -0.0872 0.9702 0.0289
-10.500 -0.7305 0.01416 0.00959 -0.0874 0.9658 0.0303
-10.250 -0.6994 0.01382 0.00918 -0.0882 0.9625 0.0311
-10.000 -0.6662 0.01369 0.00906 -0.0892 0.9598 0.0320
-9.750 -0.6378 0.01359 0.00895 -0.0893 0.9538 0.0327
-9.500 -0.6068 0.01340 0.00872 -0.0899 0.9480 0.0334
-9.250 -0.5766 0.01328 0.00856 -0.0903 0.9417 0.0342
-9.000 -0.5480 0.01305 0.00827 -0.0904 0.9332 0.0349
-8.750 -0.5197 0.01284 0.00798 -0.0905 0.9236 0.0354
-8.500 -0.4913 0.01270 0.00776 -0.0905 0.9131 0.0358
-8.250 -0.4653 0.01236 0.00735 -0.0901 0.9009 0.0364
-8.000 -0.4392 0.01208 0.00700 -0.0897 0.8887 0.0370
-7.750 -0.4121 0.01206 0.00695 -0.0894 0.8776 0.0376
-7.500 -0.3852 0.01206 0.00691 -0.0890 0.8667 0.0382
-7.250 -0.3587 0.01200 0.00681 -0.0886 0.8560 0.0387
-7.000 -0.3328 0.01179 0.00652 -0.0881 0.8462 0.0391
-6.500 -0.2815 0.01126 0.00583 -0.0870 0.8267 0.0398
-6.250 -0.2561 0.01101 0.00548 -0.0864 0.8150 0.0401
-6.000 -0.2308 0.01077 0.00515 -0.0858 0.8020 0.0405
-5.750 -0.2052 0.01055 0.00484 -0.0852 0.7892 0.0408
-5.500 -0.1795 0.01032 0.00454 -0.0846 0.7759 0.0411
-5.250 -0.1539 0.01013 0.00427 -0.0841 0.7609 0.0414
-5.000 -0.1283 0.00996 0.00401 -0.0834 0.7437 0.0417
-4.750 -0.1030 0.00982 0.00377 -0.0828 0.7236 0.0419
-4.500 -0.0780 0.00972 0.00356 -0.0820 0.6964 0.0421
-4.250 -0.0531 0.00966 0.00338 -0.0813 0.6707 0.0423
-4.000 -0.0285 0.00946 0.00307 -0.0805 0.6510 0.0429
-3.750 -0.0033 0.00929 0.00283 -0.0799 0.6351 0.0437
-3.500 0.0227 0.00919 0.00267 -0.0794 0.6224 0.0443
-3.250 0.0488 0.00911 0.00254 -0.0789 0.6118 0.0447
-3.000 0.0755 0.00902 0.00241 -0.0785 0.6020 0.0452
-2.750 0.1020 0.00895 0.00231 -0.0781 0.5927 0.0458
-2.500 0.1287 0.00887 0.00219 -0.0778 0.5838 0.0463
-2.250 0.1555 0.00880 0.00210 -0.0774 0.5756 0.0470
-2.000 0.1821 0.00875 0.00200 -0.0770 0.5649 0.0477
-1.750 0.2090 0.00869 0.00191 -0.0767 0.5557 0.0483
-1.500 0.2356 0.00866 0.00184 -0.0763 0.5449 0.0489
-1.250 0.2622 0.00864 0.00177 -0.0759 0.5324 0.0495
-1.000 0.2889 0.00862 0.00171 -0.0755 0.5196 0.0500
-0.750 0.3153 0.00863 0.00166 -0.0751 0.5045 0.0503
-0.500 0.3413 0.00862 0.00159 -0.0746 0.4874 0.0515
-0.250 0.3671 0.00863 0.00154 -0.0741 0.4697 0.0533
0.000 0.3932 0.00866 0.00152 -0.0737 0.4542 0.0546
0.250 0.4193 0.00870 0.00152 -0.0732 0.4391 0.0560
0.500 0.4453 0.00877 0.00152 -0.0727 0.4234 0.0575
0.750 0.4714 0.00883 0.00154 -0.0723 0.4097 0.0588
1.000 0.4977 0.00888 0.00156 -0.0719 0.3983 0.0600
1.250 0.5239 0.00895 0.00159 -0.0715 0.3877 0.0614
1.500 0.5503 0.00898 0.00161 -0.0711 0.3781 0.0657
1.750 0.5765 0.00903 0.00165 -0.0707 0.3690 0.0706
2.000 0.6024 0.00909 0.00170 -0.0703 0.3582 0.0801
2.250 0.6270 0.00909 0.00179 -0.0696 0.3417 0.1437
2.500 0.6463 0.00843 0.00192 -0.0683 0.3285 0.4810
2.750 0.6580 0.00761 0.00206 -0.0650 0.3201 0.8267
3.000 0.7299 0.00760 0.00230 -0.0746 0.3079 0.9826
3.250 0.7721 0.00781 0.00242 -0.0778 0.2956 0.9968
3.500 0.8083 0.00798 0.00252 -0.0797 0.2841 1.0000
3.750 0.8313 0.00813 0.00262 -0.0787 0.2758 1.0000
4.000 0.8544 0.00828 0.00273 -0.0776 0.2669 1.0000
4.250 0.8777 0.00843 0.00284 -0.0767 0.2596 1.0000
4.500 0.9010 0.00859 0.00296 -0.0757 0.2520 1.0000
4.750 0.9241 0.00876 0.00309 -0.0747 0.2435 1.0000
5.000 0.9466 0.00898 0.00324 -0.0736 0.2323 1.0000
5.250 0.9698 0.00915 0.00339 -0.0727 0.2235 1.0000
5.500 0.9925 0.00936 0.00355 -0.0717 0.2145 1.0000
5.750 1.0146 0.00961 0.00373 -0.0706 0.2027 1.0000
6.000 1.0361 0.00990 0.00395 -0.0694 0.1871 1.0000
6.250 1.0569 0.01023 0.00419 -0.0681 0.1692 1.0000
6.500 1.0754 0.01071 0.00452 -0.0664 0.1433 1.0000
6.750 1.0946 0.01115 0.00486 -0.0649 0.1239 1.0000
7.000 1.1148 0.01152 0.00516 -0.0635 0.1112 1.0000
7.250 1.1339 0.01196 0.00551 -0.0620 0.0954 1.0000
7.500 1.1484 0.01270 0.00604 -0.0597 0.0624 1.0000
7.750 1.1689 0.01303 0.00636 -0.0584 0.0579 1.0000
8.000 1.1891 0.01336 0.00669 -0.0571 0.0548 1.0000
8.250 1.2092 0.01370 0.00703 -0.0558 0.0514 1.0000
8.500 1.2300 0.01398 0.00733 -0.0546 0.0502 1.0000
8.750 1.2503 0.01426 0.00764 -0.0533 0.0491 1.0000
9.000 1.2698 0.01458 0.00797 -0.0519 0.0476 1.0000
9.250 1.2875 0.01491 0.00832 -0.0502 0.0463 1.0000
9.500 1.3034 0.01528 0.00871 -0.0481 0.0447 1.0000
9.750 1.3188 0.01568 0.00912 -0.0460 0.0430 1.0000
10.000 1.3350 0.01606 0.00953 -0.0441 0.0417 1.0000
10.250 1.3526 0.01638 0.00989 -0.0425 0.0410 1.0000
10.500 1.3696 0.01674 0.01028 -0.0409 0.0399 1.0000
10.750 1.3859 0.01715 0.01071 -0.0392 0.0383 1.0000
11.000 1.4012 0.01762 0.01121 -0.0374 0.0368 1.0000
11.250 1.4150 0.01818 0.01177 -0.0355 0.0347 1.0000
11.500 1.4308 0.01865 0.01227 -0.0339 0.0332 1.0000
11.750 1.4446 0.01924 0.01286 -0.0321 0.0298 1.0000
12.000 1.4571 0.01992 0.01354 -0.0303 0.0261 1.0000
12.250 1.4647 0.02091 0.01448 -0.0280 0.0189 1.0000
12.500 1.4725 0.02194 0.01551 -0.0259 0.0156 1.0000
12.750 1.4818 0.02293 0.01654 -0.0241 0.0140 1.0000
13.000 1.4894 0.02408 0.01773 -0.0223 0.0126 1.0000
13.250 1.4989 0.02515 0.01886 -0.0208 0.0119 1.0000
13.500 1.5067 0.02640 0.02016 -0.0193 0.0112 1.0000
13.750 1.5124 0.02787 0.02169 -0.0179 0.0103 1.0000
14.000 1.5187 0.02938 0.02326 -0.0167 0.0099 1.0000
14.250 1.5252 0.03092 0.02487 -0.0156 0.0097 1.0000
14.500 1.5308 0.03261 0.02663 -0.0147 0.0091 1.0000
14.750 1.5350 0.03451 0.02860 -0.0139 0.0088 1.0000
15.000 1.5381 0.03659 0.03075 -0.0132 0.0085 1.0000
15.250 1.5393 0.03896 0.03320 -0.0128 0.0082 1.0000
15.500 1.5401 0.04150 0.03582 -0.0125 0.0080 1.0000
15.750 1.5380 0.04445 0.03885 -0.0125 0.0077 1.0000
16.000 1.5357 0.04753 0.04202 -0.0126 0.0075 1.0000
16.250 1.5340 0.05062 0.04521 -0.0128 0.0074 1.0000
16.500 1.5306 0.05397 0.04866 -0.0132 0.0073 1.0000
16.750 1.5268 0.05743 0.05221 -0.0137 0.0071 1.0000
17.000 1.5205 0.06131 0.05619 -0.0144 0.0070 1.0000
17.250 1.5124 0.06551 0.06049 -0.0153 0.0069 1.0000
17.500 1.5037 0.06986 0.06494 -0.0163 0.0068 1.0000
17.750 1.4941 0.07443 0.06961 -0.0175 0.0067 1.0000
18.000 1.4830 0.07931 0.07458 -0.0189 0.0065 1.0000
18.250 1.4723 0.08419 0.07957 -0.0203 0.0065 1.0000
18.500 1.4603 0.08934 0.08482 -0.0219 0.0064 1.0000
18.750 1.4474 0.09472 0.09031 -0.0237 0.0064 1.0000
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Polar data table (+)
Polar graphs
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