GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 500,000 Max Cl/Cd: 94.35 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe530-il-500000.txt Download as CSV file: xf-goe530-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2578 0.10918 0.10683 -0.0395 0.9996 0.0395
-10.500 -0.2418 0.10536 0.10300 -0.0435 0.9975 0.0404
-10.250 -0.2523 0.09677 0.09441 -0.0548 0.9877 0.0425
-10.000 -0.2309 0.09413 0.09176 -0.0559 0.9834 0.0428
-9.750 -0.2110 0.09151 0.08914 -0.0575 0.9779 0.0431
-9.500 -0.1923 0.08857 0.08620 -0.0603 0.9717 0.0436
-9.250 -0.1735 0.08509 0.08271 -0.0646 0.9662 0.0442
-9.000 -0.1537 0.08113 0.07873 -0.0702 0.9588 0.0458
-8.750 -0.1483 0.06979 0.06733 -0.0904 0.9469 0.0478
-8.500 -0.1160 0.06750 0.06500 -0.0937 0.9387 0.0482
-8.250 -0.0910 0.06471 0.06216 -0.0982 0.9255 0.0487
-8.000 -0.0794 0.06192 0.05928 -0.1009 0.9086 0.0494
-7.750 -0.0815 0.05944 0.05673 -0.1010 0.8912 0.0500
-7.500 -0.1402 0.04754 0.04433 -0.1044 0.8666 0.0533
-7.250 -0.1292 0.04602 0.04279 -0.1028 0.8550 0.0535
-7.000 -0.1746 0.03348 0.02957 -0.0978 0.8415 0.0479
-6.750 -0.1612 0.03195 0.02794 -0.0960 0.8312 0.0481
-6.500 -0.1764 0.02516 0.02042 -0.0905 0.8205 0.0469
-6.250 -0.1775 0.02085 0.01531 -0.0859 0.8110 0.0477
-6.000 -0.1554 0.02024 0.01470 -0.0849 0.8024 0.0483
-5.750 -0.1303 0.02020 0.01468 -0.0843 0.7941 0.0489
-5.500 -0.1070 0.01977 0.01418 -0.0833 0.7864 0.0495
-5.250 -0.0863 0.01874 0.01296 -0.0819 0.7784 0.0503
-5.000 -0.0651 0.01756 0.01149 -0.0804 0.7713 0.0513
-4.750 -0.0434 0.01649 0.01015 -0.0789 0.7633 0.0525
-4.500 -0.0201 0.01560 0.00900 -0.0778 0.7559 0.0535
-4.250 0.0050 0.01521 0.00863 -0.0772 0.7488 0.0545
-4.000 0.0304 0.01496 0.00835 -0.0765 0.7413 0.0555
-3.750 0.0561 0.01464 0.00792 -0.0758 0.7344 0.0567
-3.500 0.0814 0.01418 0.00737 -0.0750 0.7267 0.0580
-3.250 0.1072 0.01389 0.00690 -0.0742 0.7197 0.0592
-3.000 0.1333 0.01322 0.00621 -0.0737 0.7129 0.0606
-2.750 0.1591 0.01299 0.00598 -0.0731 0.7052 0.0619
-2.500 0.1853 0.01283 0.00575 -0.0725 0.6980 0.0636
-2.250 0.2112 0.01259 0.00548 -0.0719 0.6903 0.0653
-2.000 0.2373 0.01249 0.00527 -0.0712 0.6826 0.0665
-1.750 0.2633 0.01190 0.00472 -0.0707 0.6747 0.0683
-1.500 0.2889 0.01173 0.00455 -0.0700 0.6659 0.0703
-1.250 0.3143 0.01159 0.00438 -0.0692 0.6561 0.0723
-1.000 0.3394 0.01147 0.00418 -0.0684 0.6451 0.0740
-0.750 0.3641 0.01115 0.00385 -0.0675 0.6340 0.0759
-0.500 0.3884 0.01097 0.00366 -0.0666 0.6242 0.0782
-0.250 0.4133 0.01084 0.00355 -0.0657 0.6132 0.0807
0.000 0.4376 0.01077 0.00342 -0.0648 0.6018 0.0828
0.250 0.4612 0.01065 0.00325 -0.0637 0.5895 0.0850
0.500 0.4846 0.01048 0.00311 -0.0626 0.5767 0.0883
0.750 0.5080 0.01044 0.00304 -0.0615 0.5629 0.0914
1.000 0.5310 0.01044 0.00298 -0.0603 0.5474 0.0941
1.250 0.5529 0.01039 0.00290 -0.0589 0.5313 0.0986
1.500 0.5750 0.01042 0.00288 -0.0576 0.5147 0.1036
1.750 0.5968 0.01047 0.00287 -0.0562 0.4991 0.1103
2.000 0.6188 0.01049 0.00290 -0.0548 0.4846 0.1239
2.250 0.6375 0.01025 0.00301 -0.0530 0.4721 0.2529
2.500 0.8627 0.00980 0.00410 -0.0952 0.4390 0.9978
2.750 0.8971 0.00995 0.00414 -0.0967 0.4282 1.0000
3.000 0.9200 0.01008 0.00423 -0.0957 0.4194 1.0000
3.500 0.9638 0.01043 0.00448 -0.0932 0.4026 1.0000
3.750 0.9847 0.01064 0.00462 -0.0918 0.3940 1.0000
4.000 1.0068 0.01078 0.00475 -0.0906 0.3859 1.0000
4.250 1.0275 0.01099 0.00490 -0.0892 0.3773 1.0000
4.500 1.0489 0.01116 0.00505 -0.0879 0.3690 1.0000
4.750 1.0691 0.01137 0.00521 -0.0864 0.3600 1.0000
5.000 1.0897 0.01155 0.00537 -0.0850 0.3507 1.0000
5.500 1.1285 0.01199 0.00573 -0.0817 0.3305 1.0000
5.750 1.1464 0.01226 0.00594 -0.0798 0.3215 1.0000
6.000 1.1653 0.01248 0.00614 -0.0781 0.3122 1.0000
6.250 1.1822 0.01276 0.00638 -0.0761 0.3037 1.0000
6.500 1.1996 0.01301 0.00661 -0.0741 0.2952 1.0000
6.750 1.2149 0.01332 0.00688 -0.0718 0.2873 1.0000
7.000 1.2309 0.01358 0.00712 -0.0695 0.2793 1.0000
7.250 1.2436 0.01393 0.00742 -0.0667 0.2726 1.0000
7.500 1.2592 0.01416 0.00768 -0.0645 0.2667 1.0000
7.750 1.2700 0.01446 0.00796 -0.0613 0.2612 1.0000
8.000 1.2759 0.01479 0.00826 -0.0571 0.2563 1.0000
8.250 1.2873 0.01501 0.00852 -0.0541 0.2522 1.0000
8.500 1.2971 0.01530 0.00882 -0.0508 0.2477 1.0000
8.750 1.3056 0.01568 0.00919 -0.0474 0.2434 1.0000
9.000 1.3159 0.01606 0.00957 -0.0445 0.2396 1.0000
9.250 1.3294 0.01637 0.00992 -0.0421 0.2360 1.0000
9.500 1.3413 0.01675 0.01033 -0.0395 0.2318 1.0000
9.750 1.3513 0.01725 0.01081 -0.0368 0.2275 1.0000
10.000 1.3631 0.01772 0.01130 -0.0344 0.2238 1.0000
10.250 1.3774 0.01811 0.01174 -0.0325 0.2200 1.0000
10.500 1.3900 0.01859 0.01225 -0.0304 0.2160 1.0000
10.750 1.4001 0.01922 0.01287 -0.0281 0.2117 1.0000
11.000 1.4131 0.01976 0.01345 -0.0262 0.2077 1.0000
11.250 1.4271 0.02026 0.01400 -0.0245 0.2030 1.0000
11.500 1.4379 0.02095 0.01471 -0.0225 0.1981 1.0000
11.750 1.4493 0.02165 0.01543 -0.0207 0.1927 1.0000
12.000 1.4620 0.02231 0.01612 -0.0191 0.1862 1.0000
12.250 1.4705 0.02324 0.01705 -0.0172 0.1794 1.0000
12.500 1.4809 0.02411 0.01793 -0.0156 0.1691 1.0000
12.750 1.4878 0.02525 0.01904 -0.0137 0.1560 1.0000
13.000 1.4873 0.02696 0.02064 -0.0115 0.1335 1.0000
13.250 1.4753 0.02961 0.02309 -0.0087 0.1054 1.0000
13.500 1.4681 0.03208 0.02549 -0.0066 0.0939 1.0000
13.750 1.4635 0.03445 0.02786 -0.0049 0.0881 1.0000
14.000 1.4623 0.03666 0.03012 -0.0035 0.0846 1.0000
14.250 1.4612 0.03896 0.03247 -0.0024 0.0819 1.0000
14.500 1.4578 0.04156 0.03512 -0.0014 0.0796 1.0000
14.750 1.4504 0.04468 0.03829 -0.0005 0.0773 1.0000
15.000 1.4494 0.04725 0.04094 0.0001 0.0758 1.0000
15.250 1.4490 0.04983 0.04361 0.0006 0.0742 1.0000
15.500 1.4467 0.05270 0.04656 0.0009 0.0727 1.0000
15.750 1.4419 0.05592 0.04987 0.0010 0.0713 1.0000
16.000 1.4336 0.05965 0.05366 0.0010 0.0700 1.0000
16.250 1.4230 0.06375 0.05782 0.0008 0.0687 1.0000
16.500 1.4169 0.06738 0.06154 0.0005 0.0676 1.0000
16.750 1.4165 0.07042 0.06468 0.0002 0.0664 1.0000
17.000 1.4133 0.07381 0.06816 -0.0003 0.0654 1.0000
17.250 1.4093 0.07737 0.07181 -0.0008 0.0643 1.0000
17.500 1.4043 0.08112 0.07562 -0.0015 0.0631 1.0000
17.750 1.3968 0.08519 0.07975 -0.0023 0.0621 1.0000
18.000 1.3894 0.08921 0.08381 -0.0031 0.0611 1.0000
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