EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 100,000 Max Cl/Cd: 50.88 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e558-il-100000-n5.txt Download as CSV file: xf-e558-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5121 0.11194 0.10623 -0.0464 1.0000 0.0289
-14.000 -0.5503 0.09975 0.09387 -0.0524 1.0000 0.0281
-13.750 -0.5754 0.09114 0.08510 -0.0568 1.0000 0.0282
-13.500 -0.5938 0.08433 0.07815 -0.0603 1.0000 0.0285
-13.250 -0.6064 0.07896 0.07265 -0.0628 1.0000 0.0288
-13.000 -0.6169 0.07430 0.06786 -0.0647 1.0000 0.0291
-12.750 -0.6252 0.07015 0.06358 -0.0663 1.0000 0.0294
-12.500 -0.6312 0.06657 0.05992 -0.0673 1.0000 0.0299
-12.250 -0.6330 0.06383 0.05720 -0.0677 1.0000 0.0305
-12.000 -0.6363 0.06095 0.05431 -0.0682 1.0000 0.0310
-11.750 -0.6415 0.05794 0.05126 -0.0686 1.0000 0.0318
-11.500 -0.6463 0.05512 0.04841 -0.0688 1.0000 0.0324
-11.250 -0.6526 0.05230 0.04553 -0.0687 1.0000 0.0332
-11.000 -0.6593 0.04964 0.04282 -0.0684 1.0000 0.0338
-10.750 -0.6679 0.04701 0.04014 -0.0679 1.0000 0.0343
-10.500 -0.6810 0.04433 0.03744 -0.0669 1.0000 0.0349
-10.250 -0.7008 0.04169 0.03480 -0.0654 1.0000 0.0351
-10.000 -0.7179 0.03888 0.03196 -0.0648 1.0000 0.0354
-9.750 -0.7262 0.03668 0.02971 -0.0638 1.0000 0.0361
-9.500 -0.7293 0.03486 0.02784 -0.0624 1.0000 0.0374
-9.250 -0.7213 0.03312 0.02597 -0.0624 0.9984 0.0400
-9.000 -0.6896 0.03092 0.02370 -0.0670 0.9906 0.0448
-8.750 -0.6572 0.02891 0.02158 -0.0711 0.9830 0.0527
-8.500 -0.6273 0.02710 0.01971 -0.0741 0.9739 0.0632
-8.250 -0.5974 0.02542 0.01805 -0.0769 0.9645 0.0796
-8.000 -0.5651 0.02403 0.01669 -0.0796 0.9560 0.1015
-7.750 -0.5324 0.02294 0.01562 -0.0819 0.9468 0.1260
-7.500 -0.5008 0.02213 0.01478 -0.0835 0.9367 0.1503
-7.250 -0.4633 0.02148 0.01413 -0.0861 0.9296 0.1740
-7.000 -0.4317 0.02099 0.01354 -0.0872 0.9187 0.1936
-6.750 -0.3961 0.02056 0.01300 -0.0890 0.9103 0.2117
-6.500 -0.3605 0.02018 0.01252 -0.0906 0.9010 0.2278
-6.250 -0.3253 0.01987 0.01212 -0.0920 0.8911 0.2418
-6.000 -0.2867 0.01956 0.01174 -0.0941 0.8823 0.2549
-5.750 -0.2524 0.01929 0.01135 -0.0952 0.8706 0.2667
-5.500 -0.2133 0.01896 0.01086 -0.0973 0.8611 0.2794
-5.250 -0.1785 0.01873 0.01053 -0.0985 0.8485 0.2903
-5.000 -0.1440 0.01851 0.01021 -0.0996 0.8357 0.3004
-4.750 -0.1079 0.01826 0.00975 -0.1011 0.8234 0.3118
-4.500 -0.0732 0.01809 0.00953 -0.1022 0.8104 0.3206
-4.250 -0.0418 0.01791 0.00919 -0.1027 0.7959 0.3306
-4.000 -0.0107 0.01779 0.00899 -0.1031 0.7818 0.3390
-3.750 0.0208 0.01764 0.00868 -0.1037 0.7684 0.3485
-3.250 0.0808 0.01743 0.00824 -0.1042 0.7413 0.3657
-3.000 0.1093 0.01737 0.00812 -0.1041 0.7280 0.3734
-2.750 0.1387 0.01729 0.00787 -0.1043 0.7156 0.3828
-2.500 0.1670 0.01723 0.00777 -0.1041 0.7031 0.3901
-2.250 0.1944 0.01719 0.00761 -0.1040 0.6904 0.3994
-2.000 0.2222 0.01715 0.00752 -0.1037 0.6788 0.4068
-1.750 0.2502 0.01712 0.00739 -0.1036 0.6673 0.4161
-1.500 0.2768 0.01710 0.00733 -0.1033 0.6555 0.4240
-1.250 0.3045 0.01710 0.00724 -0.1031 0.6451 0.4331
-1.000 0.3313 0.01710 0.00720 -0.1027 0.6339 0.4417
-0.750 0.3581 0.01711 0.00716 -0.1024 0.6234 0.4510
-0.500 0.3854 0.01713 0.00712 -0.1022 0.6137 0.4601
-0.250 0.4117 0.01716 0.00714 -0.1018 0.6032 0.4699
0.000 0.4390 0.01720 0.00711 -0.1015 0.5945 0.4795
0.250 0.4650 0.01725 0.00716 -0.1011 0.5841 0.4901
0.500 0.4920 0.01730 0.00718 -0.1008 0.5759 0.5002
0.750 0.5180 0.01738 0.00726 -0.1004 0.5662 0.5118
1.000 0.5446 0.01744 0.00730 -0.1000 0.5583 0.5231
1.250 0.5701 0.01752 0.00744 -0.0995 0.5491 0.5351
1.500 0.5970 0.01762 0.00749 -0.0992 0.5418 0.5488
1.750 0.6221 0.01772 0.00766 -0.0986 0.5330 0.5626
2.000 0.6482 0.01781 0.00776 -0.0982 0.5256 0.5776
2.250 0.6739 0.01793 0.00795 -0.0977 0.5178 0.5942
2.500 0.6996 0.01805 0.00811 -0.0972 0.5105 0.6126
2.750 0.7255 0.01818 0.00827 -0.0967 0.5037 0.6337
3.000 0.7500 0.01830 0.00851 -0.0960 0.4960 0.6577
3.250 0.7752 0.01841 0.00866 -0.0953 0.4900 0.6851
3.500 0.7984 0.01853 0.00895 -0.0943 0.4830 0.7180
3.750 0.8208 0.01862 0.00917 -0.0930 0.4764 0.7591
4.000 0.8428 0.01867 0.00931 -0.0915 0.4711 0.8131
4.250 0.8664 0.01868 0.00957 -0.0903 0.4640 0.9077
4.500 0.8973 0.01890 0.00975 -0.0911 0.4577 1.0000
4.750 0.9241 0.01922 0.01000 -0.0911 0.4521 1.0000
5.000 0.9489 0.01957 0.01038 -0.0907 0.4453 1.0000
5.250 0.9751 0.01989 0.01065 -0.0905 0.4397 1.0000
5.500 1.0008 0.02025 0.01099 -0.0903 0.4343 1.0000
5.750 1.0247 0.02063 0.01143 -0.0897 0.4279 1.0000
6.000 1.0501 0.02098 0.01175 -0.0894 0.4225 1.0000
6.250 1.0750 0.02137 0.01214 -0.0890 0.4171 1.0000
6.500 1.0979 0.02180 0.01265 -0.0883 0.4109 1.0000
6.750 1.1226 0.02217 0.01302 -0.0878 0.4056 1.0000
7.000 1.1467 0.02258 0.01344 -0.0873 0.4003 1.0000
7.250 1.1681 0.02305 0.01403 -0.0864 0.3941 1.0000
7.500 1.1919 0.02344 0.01442 -0.0858 0.3886 1.0000
7.750 1.2149 0.02388 0.01490 -0.0852 0.3834 1.0000
8.000 1.2346 0.02439 0.01554 -0.0840 0.3770 1.0000
8.250 1.2574 0.02480 0.01597 -0.0833 0.3715 1.0000
8.500 1.2785 0.02529 0.01652 -0.0823 0.3660 1.0000
8.750 1.2964 0.02583 0.01721 -0.0809 0.3595 1.0000
9.000 1.3181 0.02625 0.01764 -0.0800 0.3540 1.0000
9.250 1.3352 0.02681 0.01832 -0.0785 0.3478 1.0000
9.500 1.3514 0.02736 0.01898 -0.0769 0.3412 1.0000
9.750 1.3728 0.02773 0.01933 -0.0759 0.3355 1.0000
10.000 1.3821 0.02846 0.02028 -0.0734 0.3283 1.0000
10.250 1.3960 0.02895 0.02082 -0.0714 0.3219 1.0000
10.500 1.4071 0.02958 0.02154 -0.0691 0.3154 1.0000
10.750 1.4150 0.03031 0.02241 -0.0664 0.3084 1.0000
11.000 1.4282 0.03086 0.02296 -0.0645 0.3021 1.0000
11.250 1.4306 0.03189 0.02419 -0.0615 0.2945 1.0000
11.500 1.4402 0.03260 0.02492 -0.0594 0.2877 1.0000
11.750 1.4412 0.03385 0.02635 -0.0568 0.2801 1.0000
12.000 1.4459 0.03490 0.02746 -0.0546 0.2727 1.0000
12.250 1.4455 0.03643 0.02915 -0.0523 0.2647 1.0000
12.500 1.4471 0.03787 0.03065 -0.0504 0.2570 1.0000
12.750 1.4439 0.03987 0.03279 -0.0486 0.2487 1.0000
13.000 1.4432 0.04175 0.03471 -0.0471 0.2409 1.0000
13.250 1.4368 0.04438 0.03750 -0.0459 0.2324 1.0000
13.500 1.4344 0.04669 0.03982 -0.0449 0.2245 1.0000
13.750 1.4245 0.05008 0.04339 -0.0444 0.2160 1.0000
14.000 1.4183 0.05313 0.04647 -0.0440 0.2081 1.0000
14.250 1.4070 0.05706 0.05053 -0.0441 0.1997 1.0000
14.500 1.3980 0.06082 0.05437 -0.0443 0.1918 1.0000
14.750 1.3865 0.06512 0.05875 -0.0449 0.1837 1.0000
15.000 1.3753 0.06956 0.06326 -0.0456 0.1759 1.0000
15.250 1.3645 0.07408 0.06782 -0.0466 0.1680 1.0000
15.500 1.3523 0.07903 0.07287 -0.0479 0.1604 1.0000
15.750 1.3431 0.08357 0.07739 -0.0490 0.1528 1.0000
16.000 1.3297 0.08905 0.08299 -0.0508 0.1452 1.0000
16.250 1.3217 0.09359 0.08749 -0.0522 0.1377 1.0000
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Polar data table (+)
Polar graphs
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