GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 500,000 Max Cl/Cd: 95.02 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe284-il-500000-n5.txt Download as CSV file: xf-goe284-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 284 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7804 0.08639 0.08275 -0.0553 1.0000 0.0307
-15.750 -0.8080 0.07863 0.07489 -0.0603 1.0000 0.0308
-15.500 -0.8475 0.06917 0.06530 -0.0666 1.0000 0.0308
-15.250 -0.9059 0.05655 0.05249 -0.0758 1.0000 0.0307
-15.000 -0.9605 0.04080 0.03636 -0.0915 0.9749 0.0306
-14.750 -0.9740 0.03468 0.02998 -0.0980 0.9523 0.0307
-14.500 -0.9793 0.03194 0.02706 -0.0986 0.9359 0.0308
-14.250 -0.9801 0.03014 0.02511 -0.0973 0.9213 0.0309
-14.000 -0.9767 0.02880 0.02364 -0.0954 0.9076 0.0310
-13.750 -0.9664 0.02759 0.02231 -0.0942 0.8948 0.0312
-13.500 -0.9535 0.02654 0.02112 -0.0930 0.8815 0.0314
-13.250 -0.9383 0.02558 0.02003 -0.0919 0.8665 0.0316
-13.000 -0.9213 0.02471 0.01902 -0.0909 0.8502 0.0318
-12.750 -0.9028 0.02391 0.01808 -0.0900 0.8323 0.0320
-12.500 -0.8839 0.02313 0.01714 -0.0892 0.8128 0.0322
-12.250 -0.8648 0.02230 0.01618 -0.0884 0.7924 0.0325
-12.000 -0.8442 0.02156 0.01530 -0.0877 0.7719 0.0329
-11.750 -0.8224 0.02090 0.01450 -0.0871 0.7515 0.0332
-11.500 -0.7996 0.02031 0.01377 -0.0866 0.7317 0.0335
-11.250 -0.7760 0.01976 0.01309 -0.0861 0.7130 0.0339
-11.000 -0.7518 0.01926 0.01245 -0.0858 0.6957 0.0344
-10.750 -0.7270 0.01879 0.01185 -0.0854 0.6799 0.0348
-10.500 -0.7018 0.01835 0.01128 -0.0851 0.6651 0.0353
-10.250 -0.6760 0.01794 0.01076 -0.0849 0.6520 0.0358
-10.000 -0.6503 0.01750 0.01022 -0.0847 0.6404 0.0365
-9.750 -0.6245 0.01704 0.00967 -0.0845 0.6289 0.0373
-9.500 -0.5981 0.01663 0.00918 -0.0843 0.6193 0.0382
-9.250 -0.5714 0.01627 0.00873 -0.0841 0.6097 0.0391
-9.000 -0.5444 0.01594 0.00831 -0.0840 0.6020 0.0403
-8.750 -0.5175 0.01553 0.00786 -0.0839 0.5949 0.0420
-8.500 -0.4903 0.01518 0.00745 -0.0838 0.5883 0.0446
-8.000 -0.4356 0.01447 0.00678 -0.0837 0.5776 0.0588
-7.750 -0.4072 0.01430 0.00660 -0.0838 0.5724 0.0659
-7.500 -0.3785 0.01419 0.00645 -0.0838 0.5676 0.0707
-7.250 -0.3497 0.01409 0.00631 -0.0839 0.5635 0.0739
-7.000 -0.3206 0.01399 0.00618 -0.0839 0.5598 0.0769
-6.750 -0.2917 0.01388 0.00600 -0.0840 0.5560 0.0792
-6.500 -0.2626 0.01381 0.00592 -0.0841 0.5524 0.0814
-6.250 -0.2335 0.01376 0.00583 -0.0842 0.5488 0.0838
-5.750 -0.1755 0.01359 0.00554 -0.0844 0.5425 0.0870
-5.500 -0.1464 0.01347 0.00543 -0.0845 0.5398 0.0887
-5.250 -0.1173 0.01338 0.00533 -0.0846 0.5371 0.0902
-5.000 -0.0882 0.01329 0.00521 -0.0847 0.5345 0.0915
-4.750 -0.0590 0.01322 0.00509 -0.0848 0.5320 0.0930
-4.500 -0.0299 0.01315 0.00497 -0.0850 0.5296 0.0944
-4.250 -0.0008 0.01310 0.00486 -0.0851 0.5273 0.0954
-3.750 0.0571 0.01283 0.00461 -0.0853 0.5234 0.0984
-3.500 0.0863 0.01274 0.00451 -0.0855 0.5216 0.0997
-3.250 0.1156 0.01265 0.00442 -0.0856 0.5195 0.1010
-3.000 0.1450 0.01258 0.00434 -0.0858 0.5173 0.1028
-2.750 0.1743 0.01254 0.00428 -0.0860 0.5152 0.1044
-2.500 0.2036 0.01248 0.00420 -0.0861 0.5133 0.1056
-2.250 0.2324 0.01235 0.00406 -0.0863 0.5112 0.1071
-2.000 0.2613 0.01227 0.00397 -0.0864 0.5085 0.1084
-1.750 0.2901 0.01223 0.00390 -0.0865 0.5052 0.1098
-1.500 0.3195 0.01213 0.00383 -0.0867 0.5025 0.1112
-1.250 0.3489 0.01206 0.00377 -0.0869 0.4994 0.1127
-1.000 0.3781 0.01201 0.00372 -0.0871 0.4963 0.1143
-0.750 0.4072 0.01198 0.00366 -0.0872 0.4927 0.1160
-0.500 0.4360 0.01195 0.00361 -0.0873 0.4888 0.1180
-0.250 0.4649 0.01192 0.00358 -0.0875 0.4855 0.1206
0.000 0.4942 0.01185 0.00356 -0.0877 0.4828 0.1233
0.250 0.5235 0.01182 0.00354 -0.0879 0.4799 0.1262
0.500 0.5526 0.01180 0.00353 -0.0881 0.4769 0.1291
0.750 0.5816 0.01177 0.00353 -0.0883 0.4739 0.1342
1.000 0.6104 0.01176 0.00354 -0.0884 0.4710 0.1410
1.250 0.6390 0.01175 0.00356 -0.0886 0.4684 0.1525
1.750 0.6967 0.01156 0.00365 -0.0891 0.4632 0.2232
2.000 0.7253 0.01146 0.00371 -0.0893 0.4601 0.2725
2.250 0.7537 0.01139 0.00377 -0.0895 0.4566 0.3170
2.500 0.7816 0.01126 0.00383 -0.0896 0.4530 0.3834
2.750 0.8088 0.01102 0.00392 -0.0897 0.4494 0.5054
3.000 0.8355 0.01069 0.00404 -0.0896 0.4453 0.6481
3.250 0.8585 0.01033 0.00418 -0.0885 0.4405 0.8068
3.500 0.8825 0.01019 0.00432 -0.0871 0.4353 0.9397
3.750 0.9287 0.01028 0.00440 -0.0910 0.4294 0.9989
4.000 0.9561 0.01039 0.00449 -0.0909 0.4227 1.0000
4.250 0.9821 0.01054 0.00458 -0.0906 0.4157 1.0000
4.500 1.0085 0.01068 0.00468 -0.0904 0.4054 1.0000
4.750 1.0338 0.01088 0.00481 -0.0901 0.3923 1.0000
5.000 1.0580 0.01115 0.00498 -0.0895 0.3760 1.0000
5.250 1.0812 0.01148 0.00520 -0.0889 0.3594 1.0000
5.500 1.1040 0.01185 0.00547 -0.0882 0.3447 1.0000
5.750 1.1267 0.01222 0.00576 -0.0874 0.3327 1.0000
6.000 1.1495 0.01257 0.00605 -0.0868 0.3229 1.0000
6.250 1.1726 0.01290 0.00634 -0.0861 0.3154 1.0000
6.500 1.1953 0.01324 0.00664 -0.0854 0.3083 1.0000
6.750 1.2171 0.01361 0.00697 -0.0846 0.3020 1.0000
7.000 1.2394 0.01393 0.00728 -0.0839 0.2956 1.0000
7.250 1.2596 0.01434 0.00766 -0.0828 0.2892 1.0000
7.500 1.2801 0.01470 0.00800 -0.0818 0.2845 1.0000
7.750 1.3002 0.01503 0.00834 -0.0807 0.2801 1.0000
8.000 1.3178 0.01542 0.00873 -0.0792 0.2760 1.0000
8.250 1.3342 0.01589 0.00920 -0.0776 0.2720 1.0000
8.500 1.3519 0.01635 0.00966 -0.0763 0.2687 1.0000
8.750 1.3709 0.01678 0.01012 -0.0752 0.2654 1.0000
9.000 1.3888 0.01727 0.01063 -0.0741 0.2620 1.0000
9.250 1.4055 0.01785 0.01122 -0.0729 0.2586 1.0000
9.500 1.4207 0.01853 0.01191 -0.0715 0.2552 1.0000
9.750 1.4371 0.01919 0.01258 -0.0704 0.2519 1.0000
10.000 1.4542 0.01982 0.01324 -0.0695 0.2481 1.0000
10.250 1.4694 0.02059 0.01404 -0.0684 0.2442 1.0000
10.500 1.4830 0.02149 0.01495 -0.0673 0.2407 1.0000
10.750 1.4950 0.02254 0.01601 -0.0661 0.2373 1.0000
11.000 1.5108 0.02336 0.01688 -0.0653 0.2344 1.0000
11.250 1.5250 0.02433 0.01790 -0.0645 0.2310 1.0000
11.500 1.5371 0.02548 0.01909 -0.0635 0.2273 1.0000
11.750 1.5469 0.02685 0.02048 -0.0626 0.2238 1.0000
12.000 1.5566 0.02828 0.02193 -0.0617 0.2209 1.0000
12.250 1.5696 0.02947 0.02319 -0.0611 0.2182 1.0000
12.500 1.5801 0.03089 0.02466 -0.0604 0.2147 1.0000
12.750 1.5873 0.03264 0.02644 -0.0596 0.2105 1.0000
13.000 1.5910 0.03474 0.02856 -0.0588 0.2062 1.0000
13.250 1.6003 0.03636 0.03024 -0.0583 0.2018 1.0000
13.500 1.6054 0.03838 0.03231 -0.0576 0.1968 1.0000
13.750 1.6065 0.04085 0.03479 -0.0569 0.1919 1.0000
14.000 1.6109 0.04301 0.03700 -0.0564 0.1844 1.0000
14.250 1.6089 0.04586 0.03986 -0.0558 0.1752 1.0000
14.500 1.5938 0.05012 0.04405 -0.0550 0.1537 1.0000
14.750 1.5642 0.05600 0.04980 -0.0542 0.1291 1.0000
15.000 1.5489 0.06045 0.05423 -0.0536 0.1193 1.0000
15.250 1.5393 0.06436 0.05816 -0.0533 0.1134 1.0000
15.500 1.5344 0.06780 0.06163 -0.0531 0.1095 1.0000
15.750 1.5301 0.07122 0.06511 -0.0529 0.1065 1.0000
16.000 1.5259 0.07466 0.06859 -0.0529 0.1037 1.0000
16.250 1.5199 0.07840 0.07238 -0.0529 0.1013 1.0000
16.500 1.5210 0.08127 0.07531 -0.0530 0.0995 1.0000
16.750 1.5193 0.08453 0.07864 -0.0531 0.0975 1.0000
17.000 1.5171 0.08785 0.08202 -0.0533 0.0954 1.0000
17.250 1.5123 0.09158 0.08581 -0.0536 0.0936 1.0000
17.500 1.5084 0.09521 0.08950 -0.0540 0.0918 1.0000
17.750 1.5058 0.09870 0.09306 -0.0544 0.0902 1.0000
18.000 1.5067 0.10172 0.09616 -0.0548 0.0881 1.0000
18.250 1.5034 0.10536 0.09986 -0.0554 0.0859 1.0000
18.500 1.4998 0.10906 0.10362 -0.0561 0.0838 1.0000
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Polar data table (+)
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