EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 200,000 Max Cl/Cd: 70.18 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e554-il-200000-n5.txt Download as CSV file: xf-e554-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.5705 0.12995 0.12582 -0.0338 1.0000 0.0113
-16.250 -0.6173 0.11430 0.10993 -0.0420 1.0000 0.0109
-16.000 -0.6457 0.10403 0.09946 -0.0476 1.0000 0.0108
-15.750 -0.6682 0.09570 0.09092 -0.0521 1.0000 0.0108
-15.500 -0.6823 0.08940 0.08446 -0.0553 1.0000 0.0107
-15.250 -0.6972 0.08324 0.07811 -0.0584 1.0000 0.0109
-15.000 -0.7060 0.07837 0.07308 -0.0607 1.0000 0.0109
-14.750 -0.7145 0.07375 0.06830 -0.0626 1.0000 0.0110
-14.500 -0.7195 0.06982 0.06423 -0.0641 1.0000 0.0111
-14.250 -0.7250 0.06594 0.06017 -0.0654 1.0000 0.0113
-14.000 -0.7265 0.06276 0.05686 -0.0662 1.0000 0.0113
-13.750 -0.7270 0.05982 0.05378 -0.0668 1.0000 0.0115
-13.500 -0.7267 0.05708 0.05088 -0.0670 1.0000 0.0116
-13.250 -0.7242 0.05480 0.04856 -0.0671 1.0000 0.0118
-13.000 -0.7210 0.05265 0.04636 -0.0671 1.0000 0.0118
-12.750 -0.7183 0.05054 0.04422 -0.0670 1.0000 0.0121
-12.500 -0.7153 0.04851 0.04215 -0.0668 1.0000 0.0123
-12.250 -0.7112 0.04665 0.04024 -0.0664 1.0000 0.0125
-12.000 -0.7078 0.04479 0.03833 -0.0659 1.0000 0.0128
-11.750 -0.7044 0.04300 0.03650 -0.0653 1.0000 0.0131
-11.500 -0.7009 0.04130 0.03474 -0.0645 1.0000 0.0134
-11.250 -0.6978 0.03967 0.03306 -0.0635 1.0000 0.0137
-11.000 -0.6954 0.03806 0.03140 -0.0624 1.0000 0.0140
-10.750 -0.6951 0.03642 0.02972 -0.0611 1.0000 0.0144
-10.500 -0.6964 0.03481 0.02813 -0.0595 1.0000 0.0147
-10.250 -0.6954 0.03328 0.02659 -0.0583 0.9994 0.0151
-10.000 -0.6702 0.03137 0.02462 -0.0617 0.9876 0.0163
-9.750 -0.6553 0.02959 0.02277 -0.0630 0.9611 0.0173
-9.500 -0.6292 0.02771 0.02085 -0.0666 0.9375 0.0188
-9.250 -0.5933 0.02564 0.01865 -0.0724 0.9152 0.0210
-9.000 -0.5495 0.02357 0.01641 -0.0796 0.8908 0.0242
-8.750 -0.5099 0.02186 0.01453 -0.0855 0.8628 0.0283
-8.500 -0.4810 0.02062 0.01318 -0.0883 0.8349 0.0340
-8.250 -0.4586 0.01966 0.01210 -0.0892 0.8097 0.0409
-8.000 -0.4389 0.01886 0.01120 -0.0893 0.7880 0.0502
-7.750 -0.4209 0.01807 0.01037 -0.0889 0.7685 0.0637
-7.500 -0.4023 0.01731 0.00960 -0.0884 0.7516 0.0828
-7.250 -0.3835 0.01648 0.00883 -0.0880 0.7363 0.1126
-6.750 -0.3471 0.01428 0.00709 -0.0877 0.7086 0.2371
-6.500 -0.3255 0.01358 0.00674 -0.0876 0.6959 0.3296
-6.250 -0.2992 0.01352 0.00664 -0.0874 0.6835 0.3670
-6.000 -0.2720 0.01354 0.00657 -0.0873 0.6719 0.3894
-5.750 -0.2446 0.01362 0.00652 -0.0872 0.6615 0.4065
-5.500 -0.2171 0.01371 0.00649 -0.0870 0.6513 0.4197
-5.250 -0.1893 0.01377 0.00637 -0.0870 0.6420 0.4305
-5.000 -0.1617 0.01392 0.00643 -0.0868 0.6325 0.4406
-4.750 -0.1341 0.01413 0.00656 -0.0866 0.6236 0.4522
-4.500 -0.1063 0.01425 0.00650 -0.0865 0.6147 0.4616
-4.250 -0.0785 0.01420 0.00634 -0.0865 0.6067 0.4647
-4.000 -0.0507 0.01417 0.00622 -0.0865 0.5989 0.4674
-3.750 -0.0228 0.01415 0.00609 -0.0865 0.5922 0.4703
-3.500 0.0053 0.01410 0.00594 -0.0866 0.5851 0.4733
-3.250 0.0334 0.01407 0.00577 -0.0867 0.5787 0.4768
-3.000 0.0619 0.01403 0.00558 -0.0869 0.5724 0.4801
-2.750 0.0898 0.01399 0.00550 -0.0869 0.5658 0.4821
-2.500 0.1176 0.01399 0.00541 -0.0869 0.5601 0.4845
-2.250 0.1458 0.01398 0.00536 -0.0870 0.5544 0.4873
-2.000 0.1741 0.01398 0.00529 -0.0871 0.5490 0.4905
-1.750 0.2023 0.01399 0.00520 -0.0872 0.5442 0.4935
-1.500 0.2308 0.01400 0.00511 -0.0874 0.5396 0.4965
-1.250 0.2590 0.01399 0.00508 -0.0875 0.5344 0.4990
-1.000 0.2869 0.01401 0.00507 -0.0876 0.5295 0.5015
-0.750 0.3149 0.01406 0.00506 -0.0876 0.5253 0.5045
-0.500 0.3432 0.01409 0.00508 -0.0878 0.5212 0.5076
-0.250 0.3716 0.01412 0.00508 -0.0879 0.5169 0.5107
0.000 0.4000 0.01417 0.00507 -0.0881 0.5129 0.5139
0.250 0.4280 0.01423 0.00508 -0.0882 0.5092 0.5166
0.500 0.4560 0.01428 0.00514 -0.0883 0.5055 0.5193
0.750 0.4839 0.01434 0.00522 -0.0883 0.5013 0.5225
1.000 0.5120 0.01440 0.00529 -0.0884 0.4977 0.5261
1.250 0.5402 0.01449 0.00534 -0.0886 0.4944 0.5298
1.500 0.5685 0.01459 0.00539 -0.0888 0.4912 0.5332
1.750 0.5962 0.01466 0.00551 -0.0888 0.4878 0.5360
2.000 0.6238 0.01474 0.00564 -0.0888 0.4840 0.5391
2.250 0.6516 0.01483 0.00577 -0.0889 0.4807 0.5428
2.500 0.6795 0.01494 0.00588 -0.0890 0.4775 0.5471
2.750 0.7076 0.01508 0.00597 -0.0891 0.4745 0.5513
3.000 0.7350 0.01518 0.00615 -0.0891 0.4714 0.5548
3.250 0.7623 0.01529 0.00635 -0.0891 0.4680 0.5586
3.500 0.7896 0.01541 0.00652 -0.0891 0.4645 0.5629
3.750 0.8171 0.01554 0.00667 -0.0892 0.4612 0.5674
4.000 0.8446 0.01568 0.00683 -0.0892 0.4583 0.5714
4.250 0.8720 0.01584 0.00703 -0.0892 0.4555 0.5761
4.500 0.8985 0.01598 0.00729 -0.0891 0.4519 0.5814
4.750 0.9253 0.01613 0.00751 -0.0891 0.4483 0.5868
5.000 0.9519 0.01626 0.00773 -0.0889 0.4449 0.5914
5.250 0.9788 0.01642 0.00794 -0.0889 0.4418 0.5968
5.500 1.0059 0.01662 0.00815 -0.0889 0.4387 0.6029
5.750 1.0312 0.01677 0.00848 -0.0885 0.4346 0.6085
6.000 1.0567 0.01693 0.00875 -0.0883 0.4305 0.6153
6.250 1.0826 0.01709 0.00896 -0.0880 0.4265 0.6224
6.500 1.1089 0.01726 0.00917 -0.0879 0.4228 0.6290
6.750 1.1326 0.01743 0.00951 -0.0873 0.4178 0.6367
7.000 1.1568 0.01758 0.00979 -0.0867 0.4127 0.6441
7.250 1.1816 0.01774 0.01002 -0.0863 0.4083 0.6531
7.500 1.2054 0.01793 0.01034 -0.0857 0.4034 0.6623
7.750 1.2282 0.01811 0.01067 -0.0850 0.3976 0.6728
8.000 1.2512 0.01826 0.01092 -0.0843 0.3921 0.6831
8.250 1.2731 0.01846 0.01126 -0.0834 0.3858 0.6946
8.500 1.2942 0.01865 0.01158 -0.0824 0.3789 0.7074
8.750 1.3149 0.01884 0.01188 -0.0812 0.3726 0.7217
9.000 1.3341 0.01905 0.01228 -0.0799 0.3645 0.7378
9.250 1.3523 0.01927 0.01259 -0.0784 0.3569 0.7564
9.750 1.3827 0.01977 0.01340 -0.0744 0.3379 0.8042
10.000 1.3907 0.02001 0.01376 -0.0710 0.3278 0.8429
10.250 1.3963 0.02018 0.01414 -0.0672 0.3170 1.0000
10.500 1.4063 0.02077 0.01473 -0.0649 0.3043 1.0000
10.750 1.4133 0.02151 0.01546 -0.0622 0.2902 1.0000
11.000 1.4175 0.02244 0.01637 -0.0595 0.2755 1.0000
11.250 1.4192 0.02359 0.01749 -0.0568 0.2608 1.0000
11.500 1.4180 0.02502 0.01889 -0.0541 0.2457 1.0000
11.750 1.4152 0.02673 0.02058 -0.0517 0.2313 1.0000
12.000 1.4102 0.02879 0.02261 -0.0496 0.2171 1.0000
12.250 1.4040 0.03115 0.02495 -0.0479 0.2041 1.0000
12.500 1.3972 0.03378 0.02759 -0.0465 0.1915 1.0000
12.750 1.3909 0.03658 0.03039 -0.0455 0.1795 1.0000
13.000 1.3840 0.03960 0.03342 -0.0448 0.1686 1.0000
13.250 1.3760 0.04286 0.03669 -0.0443 0.1588 1.0000
13.500 1.3682 0.04623 0.04008 -0.0441 0.1492 1.0000
13.750 1.3622 0.04955 0.04344 -0.0440 0.1402 1.0000
14.000 1.3543 0.05319 0.04709 -0.0441 0.1320 1.0000
14.250 1.3480 0.05680 0.05073 -0.0444 0.1234 1.0000
14.500 1.3427 0.06039 0.05435 -0.0448 0.1160 1.0000
14.750 1.3358 0.06432 0.05829 -0.0454 0.1087 1.0000
15.000 1.3323 0.06790 0.06193 -0.0460 0.1015 1.0000
15.250 1.3259 0.07195 0.06600 -0.0468 0.0953 1.0000
15.500 1.3235 0.07560 0.06970 -0.0477 0.0888 1.0000
15.750 1.3185 0.07965 0.07377 -0.0487 0.0831 1.0000
16.000 1.3160 0.08342 0.07759 -0.0497 0.0773 1.0000
16.250 1.3118 0.08752 0.08173 -0.0509 0.0724 1.0000
16.500 1.3096 0.09139 0.08566 -0.0520 0.0674 1.0000
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Polar data table (+)
Polar graphs
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