EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 100,000 Max Cl/Cd: 41.16 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e558-il-100000.txt Download as CSV file: xf-e558-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 558 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6076 0.07248 0.06695 -0.0730 1.0000 0.0542
-12.000 -0.6321 0.06646 0.06084 -0.0763 1.0000 0.0538
-11.750 -0.6599 0.06083 0.05509 -0.0793 1.0000 0.0535
-11.500 -0.6841 0.05646 0.05061 -0.0809 1.0000 0.0533
-11.250 -0.7099 0.05297 0.04701 -0.0808 1.0000 0.0532
-11.000 -0.7325 0.05031 0.04425 -0.0792 1.0000 0.0530
-10.750 -0.7482 0.04750 0.04123 -0.0775 1.0000 0.0532
-10.500 -0.7596 0.04486 0.03832 -0.0757 1.0000 0.0538
-10.250 -0.7655 0.04245 0.03557 -0.0738 1.0000 0.0544
-10.000 -0.7572 0.04032 0.03356 -0.0722 1.0000 0.0562
-9.750 -0.7510 0.03873 0.03194 -0.0704 1.0000 0.0581
-9.500 -0.7448 0.03694 0.03000 -0.0686 1.0000 0.0600
-9.250 -0.7380 0.03506 0.02787 -0.0668 1.0000 0.0621
-9.000 -0.7282 0.03328 0.02607 -0.0650 1.0000 0.0644
-8.750 -0.7175 0.03200 0.02487 -0.0633 1.0000 0.0679
-8.500 -0.7065 0.03062 0.02325 -0.0619 1.0000 0.0727
-8.250 -0.6954 0.02937 0.02219 -0.0605 1.0000 0.0798
-8.000 -0.6833 0.02805 0.02092 -0.0595 1.0000 0.0891
-7.750 -0.6700 0.02673 0.01965 -0.0587 1.0000 0.1038
-7.500 -0.6556 0.02555 0.01859 -0.0583 1.0000 0.1261
-7.250 -0.6174 0.02493 0.01794 -0.0622 0.9941 0.1640
-7.000 -0.5703 0.02509 0.01820 -0.0669 0.9844 0.1978
-6.750 -0.5253 0.02551 0.01859 -0.0708 0.9740 0.2252
-6.500 -0.4821 0.02581 0.01894 -0.0739 0.9634 0.2471
-6.250 -0.4397 0.02611 0.01928 -0.0766 0.9531 0.2662
-6.000 -0.3921 0.02627 0.01942 -0.0801 0.9449 0.2848
-5.750 -0.3545 0.02617 0.01926 -0.0819 0.9333 0.3001
-5.500 -0.3152 0.02596 0.01895 -0.0840 0.9225 0.3152
-5.250 -0.2673 0.02566 0.01854 -0.0875 0.9153 0.3311
-5.000 -0.2313 0.02550 0.01834 -0.0887 0.9035 0.3437
-4.750 -0.1806 0.02511 0.01793 -0.0923 0.8981 0.3571
-4.500 -0.1457 0.02468 0.01741 -0.0935 0.8861 0.3692
-4.250 -0.0921 0.02398 0.01654 -0.0980 0.8812 0.3842
-4.000 -0.0578 0.02372 0.01629 -0.0987 0.8689 0.3943
-3.750 -0.0070 0.02302 0.01549 -0.1024 0.8631 0.4072
-3.500 0.0263 0.02256 0.01482 -0.1035 0.8496 0.4195
-3.250 0.0627 0.02223 0.01453 -0.1044 0.8382 0.4289
-3.000 0.1048 0.02164 0.01379 -0.1068 0.8284 0.4409
-2.750 0.1348 0.02141 0.01349 -0.1068 0.8142 0.4512
-2.500 0.1662 0.02111 0.01312 -0.1072 0.8012 0.4611
-2.250 0.2019 0.02079 0.01260 -0.1084 0.7899 0.4733
-2.000 0.2297 0.02061 0.01244 -0.1079 0.7762 0.4820
-1.750 0.2573 0.02047 0.01215 -0.1078 0.7625 0.4935
-1.500 0.2859 0.02035 0.01201 -0.1076 0.7504 0.5028
-1.250 0.3165 0.02017 0.01170 -0.1078 0.7388 0.5142
-1.000 0.3411 0.02016 0.01167 -0.1070 0.7254 0.5249
-0.750 0.3685 0.02009 0.01156 -0.1067 0.7139 0.5354
-0.500 0.3982 0.02000 0.01133 -0.1068 0.7031 0.5483
-0.250 0.4217 0.02004 0.01143 -0.1058 0.6908 0.5588
0.000 0.4501 0.02001 0.01133 -0.1057 0.6808 0.5711
0.250 0.4762 0.02003 0.01130 -0.1053 0.6696 0.5847
0.500 0.5011 0.02010 0.01140 -0.1045 0.6591 0.5971
0.750 0.5292 0.02008 0.01135 -0.1042 0.6498 0.6108
1.000 0.5527 0.02021 0.01153 -0.1034 0.6392 0.6254
1.250 0.5819 0.02021 0.01147 -0.1033 0.6310 0.6418
1.500 0.6040 0.02038 0.01173 -0.1023 0.6204 0.6584
1.750 0.6327 0.02040 0.01171 -0.1020 0.6130 0.6771
2.000 0.6531 0.02061 0.01208 -0.1007 0.6031 0.6964
2.250 0.6804 0.02063 0.01208 -0.1001 0.5957 0.7194
2.500 0.7006 0.02086 0.01246 -0.0987 0.5865 0.7457
2.750 0.7250 0.02089 0.01255 -0.0975 0.5793 0.7760
3.000 0.7435 0.02106 0.01289 -0.0954 0.5716 0.8146
3.250 0.7605 0.02102 0.01302 -0.0927 0.5641 0.8698
3.500 0.8053 0.02097 0.01303 -0.0960 0.5563 1.0000
3.750 0.8346 0.02147 0.01345 -0.0973 0.5478 1.0000
4.000 0.8688 0.02178 0.01354 -0.0987 0.5419 1.0000
4.250 0.8888 0.02245 0.01428 -0.0979 0.5333 1.0000
4.500 0.9183 0.02278 0.01451 -0.0982 0.5267 1.0000
4.750 0.9428 0.02338 0.01510 -0.0979 0.5201 1.0000
5.000 0.9658 0.02395 0.01570 -0.0973 0.5127 1.0000
5.250 0.9977 0.02424 0.01587 -0.0979 0.5071 1.0000
5.500 1.0147 0.02509 0.01685 -0.0965 0.4995 1.0000
5.750 1.0408 0.02555 0.01731 -0.0963 0.4932 1.0000
6.000 1.0701 0.02601 0.01769 -0.0965 0.4877 1.0000
6.250 1.0852 0.02690 0.01875 -0.0948 0.4800 1.0000
6.500 1.1142 0.02726 0.01907 -0.0950 0.4742 1.0000
6.750 1.1353 0.02804 0.01992 -0.0941 0.4680 1.0000
7.000 1.1540 0.02880 0.02078 -0.0929 0.4608 1.0000
7.250 1.1864 0.02903 0.02094 -0.0934 0.4555 1.0000
7.500 1.1985 0.03016 0.02227 -0.0914 0.4484 1.0000
7.750 1.2214 0.03072 0.02287 -0.0907 0.4418 1.0000
8.000 1.2576 0.03087 0.02291 -0.0917 0.4367 1.0000
8.250 1.2600 0.03230 0.02465 -0.0885 0.4287 1.0000
8.500 1.2895 0.03252 0.02485 -0.0886 0.4226 1.0000
8.750 1.3070 0.03339 0.02583 -0.0872 0.4160 1.0000
9.000 1.3219 0.03421 0.02678 -0.0855 0.4086 1.0000
9.250 1.3648 0.03386 0.02628 -0.0872 0.4027 1.0000
9.500 1.3591 0.03556 0.02830 -0.0830 0.3946 1.0000
9.750 1.3945 0.03528 0.02798 -0.0836 0.3877 1.0000
10.000 1.4006 0.03650 0.02938 -0.0809 0.3802 1.0000
10.250 1.4252 0.03661 0.02952 -0.0802 0.3725 1.0000
10.500 1.4437 0.03714 0.03012 -0.0788 0.3651 1.0000
10.750 1.4572 0.03765 0.03076 -0.0768 0.3568 1.0000
11.000 1.4825 0.03773 0.03084 -0.0762 0.3489 1.0000
11.250 1.4891 0.03841 0.03167 -0.0733 0.3405 1.0000
11.500 1.5118 0.03842 0.03168 -0.0723 0.3320 1.0000
11.750 1.5187 0.03891 0.03228 -0.0694 0.3233 1.0000
12.000 1.5304 0.03921 0.03263 -0.0670 0.3147 1.0000
12.250 1.5421 0.03929 0.03274 -0.0646 0.3057 1.0000
12.500 1.5390 0.04029 0.03385 -0.0608 0.2977 1.0000
12.750 1.5725 0.03945 0.03286 -0.0608 0.2868 1.0000
13.000 1.5400 0.04196 0.03567 -0.0547 0.2804 1.0000
13.250 1.5626 0.04162 0.03523 -0.0536 0.2699 1.0000
13.500 1.5357 0.04436 0.03823 -0.0494 0.2627 1.0000
13.750 1.5450 0.04494 0.03876 -0.0477 0.2527 1.0000
14.000 1.5326 0.04719 0.04113 -0.0453 0.2438 1.0000
14.250 1.5232 0.04952 0.04354 -0.0435 0.2347 1.0000
14.500 1.5279 0.05062 0.04453 -0.0423 0.2237 1.0000
14.750 1.5020 0.05497 0.04911 -0.0412 0.2158 1.0000
15.000 1.1232 0.11815 0.11284 -0.0636 0.2127 1.0000
15.250 1.1387 0.11833 0.11310 -0.0630 0.2066 1.0000
15.500 1.1852 0.11211 0.10701 -0.0594 0.2015 1.0000
15.750 1.4597 0.06864 0.06285 -0.0405 0.1773 1.0000
16.000 1.4485 0.07267 0.06687 -0.0411 0.1680 1.0000
16.250 1.4309 0.07794 0.07226 -0.0423 0.1598 1.0000
16.500 1.4274 0.08121 0.07541 -0.0428 0.1501 1.0000
16.750 1.4101 0.08686 0.08120 -0.0446 0.1426 1.0000
17.000 1.4024 0.09112 0.08544 -0.0457 0.1344 1.0000
17.250 1.4063 0.09347 0.08759 -0.0459 0.1248 1.0000
17.500 1.3824 0.10078 0.09519 -0.0489 0.1195 1.0000
17.750 1.3864 0.10323 0.09747 -0.0493 0.1109 1.0000
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Polar data table (+)
Polar graphs
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