GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 200,000 Max Cl/Cd: 69.04 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe284-il-200000.txt Download as CSV file: xf-goe284-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2617 0.11842 0.11490 -0.0523 0.9934 0.0884
-11.250 -0.2279 0.11528 0.11175 -0.0526 0.9768 0.0890
-11.000 -0.6124 0.03699 0.03188 -0.1042 0.9476 0.0662
-10.750 -0.6010 0.03503 0.02973 -0.1034 0.9307 0.0673
-10.500 -0.5767 0.03535 0.03015 -0.1021 0.9140 0.0682
-10.250 -0.5593 0.03494 0.02970 -0.1004 0.8956 0.0694
-10.000 -0.5509 0.03304 0.02751 -0.0985 0.8764 0.0711
-9.750 -0.5481 0.02982 0.02367 -0.0965 0.8574 0.0736
-9.500 -0.5244 0.02991 0.02382 -0.0952 0.8380 0.0748
-9.250 -0.5023 0.02966 0.02349 -0.0941 0.8185 0.0765
-9.000 -0.4892 0.02757 0.02079 -0.0926 0.8004 0.0806
-8.750 -0.4631 0.02777 0.02106 -0.0919 0.7825 0.0823
-8.500 -0.4386 0.02771 0.02089 -0.0912 0.7660 0.0853
-8.250 -0.4167 0.02695 0.01985 -0.0906 0.7505 0.0898
-8.000 -0.3896 0.02727 0.02018 -0.0903 0.7372 0.0931
-7.750 -0.3672 0.02660 0.01917 -0.0896 0.7264 0.0987
-7.500 -0.3392 0.02685 0.01951 -0.0896 0.7153 0.1020
-7.250 -0.3163 0.02620 0.01840 -0.0890 0.7068 0.1077
-7.000 -0.2887 0.02603 0.01837 -0.0891 0.6981 0.1106
-6.750 -0.2618 0.02590 0.01815 -0.0890 0.6904 0.1147
-6.500 -0.2372 0.02528 0.01713 -0.0886 0.6843 0.1190
-6.250 -0.2098 0.02489 0.01687 -0.0888 0.6772 0.1221
-6.000 -0.1824 0.02467 0.01659 -0.0888 0.6710 0.1256
-5.750 -0.1557 0.02432 0.01594 -0.0886 0.6659 0.1291
-5.500 -0.1291 0.02353 0.01502 -0.0886 0.6608 0.1322
-5.250 -0.1014 0.02326 0.01483 -0.0888 0.6558 0.1359
-5.000 -0.0734 0.02313 0.01465 -0.0889 0.6513 0.1402
-4.750 -0.0454 0.02308 0.01434 -0.0888 0.6475 0.1438
-4.500 -0.0183 0.02216 0.01333 -0.0890 0.6439 0.1467
-4.250 0.0098 0.02163 0.01282 -0.0891 0.6399 0.1487
-4.000 0.0382 0.02118 0.01230 -0.0893 0.6358 0.1504
-3.750 0.0667 0.02079 0.01184 -0.0893 0.6320 0.1524
-3.500 0.0953 0.02045 0.01138 -0.0894 0.6287 0.1544
-3.250 0.1241 0.02018 0.01098 -0.0895 0.6258 0.1560
-3.000 0.1528 0.01992 0.01066 -0.0897 0.6229 0.1576
-2.750 0.1816 0.01971 0.01041 -0.0898 0.6198 0.1590
-2.500 0.2099 0.01922 0.00993 -0.0900 0.6164 0.1614
-2.250 0.2383 0.01892 0.00966 -0.0901 0.6131 0.1641
-2.000 0.2670 0.01873 0.00947 -0.0902 0.6101 0.1668
-1.750 0.2958 0.01861 0.00931 -0.0903 0.6077 0.1697
-1.500 0.3245 0.01861 0.00925 -0.0904 0.6050 0.1728
-1.250 0.3526 0.01851 0.00919 -0.0904 0.6015 0.1758
-1.000 0.3798 0.01819 0.00900 -0.0904 0.5969 0.1808
-0.750 0.4080 0.01802 0.00884 -0.0903 0.5921 0.1863
-0.500 0.4368 0.01792 0.00865 -0.0903 0.5879 0.1924
-0.250 0.4646 0.01784 0.00864 -0.0903 0.5844 0.2009
0.000 0.4919 0.01775 0.00868 -0.0903 0.5805 0.2131
0.250 0.5191 0.01758 0.00871 -0.0903 0.5765 0.2374
0.500 0.5458 0.01717 0.00869 -0.0902 0.5727 0.3258
0.750 0.5668 0.01618 0.00876 -0.0891 0.5693 0.6102
1.000 0.5913 0.01570 0.00901 -0.0867 0.5661 0.9013
1.250 0.6543 0.01580 0.00916 -0.0936 0.5611 0.9924
1.500 0.6907 0.01593 0.00923 -0.0955 0.5564 1.0000
1.750 0.7154 0.01604 0.00924 -0.0949 0.5525 1.0000
2.000 0.7413 0.01616 0.00923 -0.0944 0.5490 1.0000
2.250 0.7672 0.01641 0.00935 -0.0940 0.5455 1.0000
2.500 0.7902 0.01658 0.00957 -0.0933 0.5408 1.0000
2.750 0.8150 0.01673 0.00970 -0.0927 0.5362 1.0000
3.000 0.8415 0.01684 0.00972 -0.0924 0.5321 1.0000
3.250 0.8694 0.01696 0.00972 -0.0923 0.5285 1.0000
3.500 0.8946 0.01721 0.00996 -0.0919 0.5242 1.0000
3.750 0.9188 0.01737 0.01016 -0.0913 0.5187 1.0000
4.000 0.9454 0.01744 0.01018 -0.0911 0.5138 1.0000
4.250 0.9742 0.01749 0.01011 -0.0911 0.5095 1.0000
4.500 0.9987 0.01769 0.01033 -0.0906 0.5040 1.0000
4.750 1.0233 0.01779 0.01046 -0.0901 0.4978 1.0000
5.000 1.0510 0.01780 0.01039 -0.0900 0.4926 1.0000
5.250 1.0782 0.01792 0.01045 -0.0898 0.4876 1.0000
5.500 1.1007 0.01806 0.01068 -0.0890 0.4803 1.0000
5.750 1.1276 0.01806 0.01062 -0.0888 0.4744 1.0000
6.000 1.1532 0.01817 0.01070 -0.0884 0.4682 1.0000
6.250 1.1758 0.01828 0.01087 -0.0876 0.4601 1.0000
6.500 1.2029 0.01827 0.01076 -0.0874 0.4540 1.0000
6.750 1.2234 0.01846 0.01104 -0.0863 0.4448 1.0000
7.000 1.2482 0.01847 0.01097 -0.0857 0.4372 1.0000
7.250 1.2681 0.01868 0.01124 -0.0845 0.4273 1.0000
7.500 1.2917 0.01877 0.01123 -0.0838 0.4194 1.0000
7.750 1.3101 0.01908 0.01162 -0.0824 0.4094 1.0000
8.000 1.3324 0.01930 0.01172 -0.0816 0.4020 1.0000
8.250 1.3498 0.01971 0.01219 -0.0802 0.3927 1.0000
8.500 1.3707 0.02003 0.01239 -0.0792 0.3857 1.0000
8.750 1.3865 0.02053 0.01296 -0.0775 0.3775 1.0000
9.000 1.4056 0.02096 0.01328 -0.0764 0.3709 1.0000
9.250 1.4204 0.02152 0.01388 -0.0746 0.3644 1.0000
9.500 1.4352 0.02206 0.01442 -0.0728 0.3585 1.0000
9.750 1.4568 0.02259 0.01483 -0.0722 0.3537 1.0000
10.000 1.4696 0.02328 0.01562 -0.0703 0.3490 1.0000
10.250 1.4844 0.02396 0.01634 -0.0688 0.3444 1.0000
10.500 1.5032 0.02457 0.01692 -0.0679 0.3402 1.0000
10.750 1.5260 0.02517 0.01746 -0.0675 0.3362 1.0000
11.000 1.5362 0.02603 0.01844 -0.0656 0.3323 1.0000
11.250 1.5501 0.02682 0.01931 -0.0642 0.3286 1.0000
11.500 1.5668 0.02754 0.02004 -0.0632 0.3250 1.0000
11.750 1.5945 0.02802 0.02041 -0.0635 0.3210 1.0000
12.000 1.6001 0.02912 0.02166 -0.0613 0.3176 1.0000
12.250 1.6080 0.03019 0.02285 -0.0596 0.3139 1.0000
12.500 1.6194 0.03113 0.02384 -0.0583 0.3099 1.0000
12.750 1.6402 0.03172 0.02435 -0.0578 0.3056 1.0000
13.000 1.6472 0.03296 0.02570 -0.0562 0.3018 1.0000
13.250 1.6490 0.03446 0.02735 -0.0544 0.2982 1.0000
13.500 1.6563 0.03574 0.02870 -0.0531 0.2944 1.0000
13.750 1.6703 0.03665 0.02961 -0.0522 0.2906 1.0000
14.000 1.6843 0.03765 0.03062 -0.0514 0.2866 1.0000
14.250 1.6790 0.03983 0.03301 -0.0497 0.2832 1.0000
14.500 1.6799 0.04171 0.03500 -0.0485 0.2794 1.0000
14.750 1.6872 0.04313 0.03647 -0.0476 0.2756 1.0000
15.000 1.7055 0.04377 0.03705 -0.0471 0.2713 1.0000
15.250 1.6887 0.04720 0.04073 -0.0457 0.2673 1.0000
15.500 1.6832 0.04987 0.04353 -0.0449 0.2628 1.0000
15.750 1.6896 0.05148 0.04514 -0.0444 0.2581 1.0000
16.000 1.6894 0.05386 0.04760 -0.0438 0.2538 1.0000
16.250 1.6754 0.05780 0.05175 -0.0435 0.2492 1.0000
16.500 1.6725 0.06062 0.05462 -0.0434 0.2439 1.0000
16.750 1.6715 0.06328 0.05732 -0.0432 0.2385 1.0000
17.000 1.6530 0.06822 0.06247 -0.0436 0.2325 1.0000
17.250 1.6555 0.07056 0.06477 -0.0436 0.2262 1.0000
17.500 1.6337 0.07621 0.07064 -0.0443 0.2198 1.0000
17.750 1.6271 0.07992 0.07438 -0.0447 0.2126 1.0000
18.000 1.6073 0.08558 0.08022 -0.0456 0.2048 1.0000
18.250 1.5990 0.08965 0.08427 -0.0463 0.1964 1.0000
18.500 1.5757 0.09602 0.09080 -0.0476 0.1865 1.0000
18.750 1.5558 0.10200 0.09686 -0.0490 0.1759 1.0000
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Polar data table (+)
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