GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 500,000 Max Cl/Cd: 98.44 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe526-il-500000.txt Download as CSV file: xf-goe526-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 526 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3408 0.10868 0.10616 -0.0441 1.0000 0.0428
-11.000 -0.3337 0.10682 0.10433 -0.0433 1.0000 0.0431
-10.750 -0.6753 0.03474 0.03104 -0.0915 0.9825 0.0371
-10.500 -0.6627 0.03122 0.02728 -0.0926 0.9755 0.0376
-10.250 -0.6348 0.02959 0.02556 -0.0944 0.9720 0.0381
-10.000 -0.6042 0.02814 0.02399 -0.0964 0.9698 0.0386
-9.750 -0.5799 0.02649 0.02216 -0.0971 0.9643 0.0391
-9.500 -0.5534 0.02477 0.02022 -0.0982 0.9591 0.0398
-9.250 -0.5246 0.02306 0.01825 -0.0995 0.9552 0.0405
-9.000 -0.5016 0.02183 0.01677 -0.0992 0.9465 0.0413
-8.750 -0.4740 0.02069 0.01537 -0.0997 0.9402 0.0419
-8.500 -0.4524 0.01940 0.01385 -0.0989 0.9306 0.0424
-8.250 -0.4267 0.01812 0.01247 -0.0989 0.9231 0.0431
-8.000 -0.4034 0.01750 0.01180 -0.0981 0.9128 0.0437
-7.750 -0.3764 0.01689 0.01110 -0.0980 0.9049 0.0444
-7.500 -0.3535 0.01634 0.01045 -0.0970 0.8945 0.0452
-7.250 -0.3275 0.01581 0.00979 -0.0966 0.8867 0.0461
-7.000 -0.3036 0.01537 0.00924 -0.0957 0.8772 0.0471
-6.750 -0.2774 0.01501 0.00871 -0.0952 0.8696 0.0478
-6.500 -0.2548 0.01411 0.00775 -0.0942 0.8608 0.0489
-6.250 -0.2289 0.01367 0.00727 -0.0937 0.8539 0.0500
-6.000 -0.2041 0.01334 0.00691 -0.0930 0.8463 0.0511
-5.750 -0.1784 0.01302 0.00650 -0.0924 0.8388 0.0524
-5.500 -0.1527 0.01275 0.00614 -0.0918 0.8312 0.0538
-5.250 -0.1284 0.01227 0.00561 -0.0910 0.8231 0.0556
-5.000 -0.1027 0.01199 0.00530 -0.0904 0.8160 0.0574
-4.750 -0.0775 0.01174 0.00504 -0.0897 0.8083 0.0595
-4.500 -0.0510 0.01156 0.00475 -0.0891 0.8014 0.0614
-4.250 -0.0268 0.01116 0.00437 -0.0883 0.7942 0.0643
-4.000 -0.0009 0.01097 0.00415 -0.0877 0.7870 0.0673
-3.750 0.0254 0.01080 0.00392 -0.0872 0.7809 0.0708
-3.500 0.0506 0.01055 0.00372 -0.0865 0.7746 0.0753
-3.250 0.0772 0.01043 0.00355 -0.0860 0.7688 0.0796
-3.000 0.1032 0.01023 0.00336 -0.0855 0.7635 0.0858
-2.750 0.1290 0.01006 0.00322 -0.0849 0.7575 0.0924
-2.500 0.1555 0.00995 0.00311 -0.0844 0.7517 0.1004
-2.250 0.1822 0.00984 0.00302 -0.0840 0.7464 0.1102
-2.000 0.2082 0.00972 0.00295 -0.0835 0.7406 0.1202
-1.750 0.2349 0.00967 0.00289 -0.0830 0.7347 0.1303
-1.500 0.2618 0.00961 0.00284 -0.0826 0.7290 0.1414
-1.250 0.2876 0.00950 0.00278 -0.0821 0.7227 0.1514
-1.000 0.3142 0.00946 0.00272 -0.0816 0.7164 0.1609
-0.750 0.3405 0.00937 0.00266 -0.0811 0.7107 0.1719
-0.500 0.3664 0.00929 0.00261 -0.0805 0.7040 0.1823
-0.250 0.3925 0.00921 0.00254 -0.0800 0.6973 0.1948
0.000 0.4179 0.00911 0.00250 -0.0793 0.6896 0.2106
0.250 0.4429 0.00899 0.00245 -0.0786 0.6807 0.2345
0.500 0.4668 0.00877 0.00243 -0.0777 0.6720 0.2930
0.750 0.4836 0.00810 0.00244 -0.0756 0.6629 0.5204
1.000 0.5296 0.00721 0.00275 -0.0788 0.6525 0.9416
1.250 0.5759 0.00742 0.00288 -0.0822 0.6414 0.9671
1.500 0.6301 0.00762 0.00298 -0.0875 0.6264 0.9790
1.750 0.6845 0.00777 0.00304 -0.0930 0.6091 0.9878
2.000 0.7397 0.00789 0.00305 -0.0988 0.5890 0.9961
2.250 0.7803 0.00797 0.00303 -0.1015 0.5656 1.0000
2.500 0.7997 0.00814 0.00307 -0.0997 0.5432 1.0000
2.750 0.8190 0.00832 0.00314 -0.0979 0.5211 1.0000
3.000 0.8380 0.00852 0.00323 -0.0961 0.4996 1.0000
3.250 0.8568 0.00873 0.00334 -0.0943 0.4807 1.0000
3.500 0.8758 0.00894 0.00346 -0.0925 0.4650 1.0000
3.750 0.8949 0.00915 0.00359 -0.0907 0.4519 1.0000
4.000 0.9134 0.00939 0.00375 -0.0888 0.4394 1.0000
4.250 0.9333 0.00956 0.00389 -0.0872 0.4289 1.0000
4.500 0.9523 0.00976 0.00404 -0.0854 0.4196 1.0000
4.750 0.9711 0.00997 0.00421 -0.0835 0.4092 1.0000
5.000 0.9903 0.01016 0.00437 -0.0818 0.4000 1.0000
5.250 1.0087 0.01037 0.00454 -0.0799 0.3910 1.0000
5.500 1.0280 0.01054 0.00471 -0.0781 0.3826 1.0000
5.750 1.0462 0.01076 0.00489 -0.0762 0.3741 1.0000
6.000 1.0653 0.01093 0.00506 -0.0744 0.3658 1.0000
6.250 1.0827 0.01116 0.00525 -0.0724 0.3563 1.0000
6.500 1.1015 0.01133 0.00544 -0.0706 0.3470 1.0000
6.750 1.1179 0.01159 0.00565 -0.0683 0.3373 1.0000
7.000 1.1363 0.01178 0.00584 -0.0665 0.3268 1.0000
7.250 1.1530 0.01202 0.00606 -0.0643 0.3155 1.0000
7.500 1.1682 0.01231 0.00631 -0.0619 0.3025 1.0000
7.750 1.1810 0.01262 0.00657 -0.0590 0.2864 1.0000
8.000 1.1916 0.01296 0.00684 -0.0558 0.2668 1.0000
8.250 1.1995 0.01344 0.00719 -0.0521 0.2425 1.0000
8.500 1.2073 0.01401 0.00764 -0.0486 0.2167 1.0000
9.000 1.2253 0.01527 0.00869 -0.0425 0.1841 1.0000
9.250 1.2374 0.01582 0.00922 -0.0400 0.1750 1.0000
9.500 1.2478 0.01649 0.00985 -0.0374 0.1668 1.0000
9.750 1.2624 0.01699 0.01037 -0.0356 0.1601 1.0000
10.000 1.2733 0.01770 0.01105 -0.0332 0.1530 1.0000
10.250 1.2884 0.01823 0.01162 -0.0315 0.1467 1.0000
10.500 1.2999 0.01896 0.01233 -0.0295 0.1390 1.0000
10.750 1.3146 0.01956 0.01296 -0.0279 0.1310 1.0000
11.000 1.3259 0.02037 0.01374 -0.0260 0.1221 1.0000
11.250 1.3376 0.02118 0.01452 -0.0243 0.1118 1.0000
11.500 1.3483 0.02210 0.01542 -0.0225 0.1022 1.0000
11.750 1.3575 0.02315 0.01644 -0.0207 0.0953 1.0000
12.000 1.3647 0.02436 0.01763 -0.0189 0.0891 1.0000
12.250 1.3735 0.02552 0.01882 -0.0173 0.0845 1.0000
12.500 1.3801 0.02687 0.02017 -0.0157 0.0804 1.0000
12.750 1.3846 0.02842 0.02175 -0.0140 0.0770 1.0000
13.000 1.3944 0.02963 0.02302 -0.0128 0.0739 1.0000
13.250 1.4005 0.03115 0.02458 -0.0115 0.0712 1.0000
13.500 1.3996 0.03329 0.02672 -0.0099 0.0683 1.0000
13.750 1.4100 0.03455 0.02807 -0.0091 0.0662 1.0000
14.000 1.4167 0.03616 0.02975 -0.0081 0.0639 1.0000
14.250 1.4204 0.03807 0.03169 -0.0071 0.0620 1.0000
14.500 1.4178 0.04062 0.03427 -0.0061 0.0599 1.0000
14.750 1.4264 0.04220 0.03595 -0.0055 0.0581 1.0000
15.000 1.4316 0.04414 0.03795 -0.0049 0.0565 1.0000
15.250 1.4346 0.04634 0.04021 -0.0044 0.0547 1.0000
15.500 1.4333 0.04905 0.04296 -0.0039 0.0533 1.0000
15.750 1.4307 0.05196 0.04593 -0.0036 0.0519 1.0000
16.000 1.4358 0.05415 0.04822 -0.0034 0.0505 1.0000
16.250 1.4382 0.05665 0.05081 -0.0034 0.0491 1.0000
16.500 1.4391 0.05940 0.05362 -0.0034 0.0479 1.0000
16.750 1.4362 0.06264 0.05691 -0.0036 0.0468 1.0000
17.000 1.4286 0.06645 0.06076 -0.0039 0.0455 1.0000
17.250 1.4306 0.06924 0.06367 -0.0042 0.0446 1.0000
17.500 1.4313 0.07225 0.06678 -0.0047 0.0434 1.0000
17.750 1.4292 0.07562 0.07023 -0.0053 0.0425 1.0000
18.000 1.4267 0.07908 0.07376 -0.0060 0.0415 1.0000
18.250 1.4211 0.08297 0.07769 -0.0068 0.0406 1.0000
18.500 1.4131 0.08712 0.08187 -0.0077 0.0395 1.0000
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Polar data table (+)
Polar graphs
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