EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 50,000 Max Cl/Cd: 16.03 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e857-il-50000-n5.txt Download as CSV file: xf-e857-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 857 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3272 0.11544 0.10860 -0.0577 1.0000 0.0624
-11.750 -0.4794 0.08227 0.07519 -0.0736 1.0000 0.0587
-11.500 -0.5121 0.07684 0.06970 -0.0746 1.0000 0.0586
-11.250 -0.5411 0.07273 0.06553 -0.0745 1.0000 0.0586
-11.000 -0.5710 0.06937 0.06211 -0.0734 1.0000 0.0586
-10.750 -0.5965 0.06662 0.05931 -0.0721 0.9993 0.0586
-10.500 -0.5726 0.06402 0.05672 -0.0763 0.9906 0.0613
-10.250 -0.5664 0.05997 0.05241 -0.0812 0.9787 0.0636
-10.000 -0.5685 0.05593 0.04793 -0.0847 0.9636 0.0661
-9.750 -0.5473 0.05409 0.04616 -0.0865 0.9514 0.0696
-9.500 -0.5347 0.05132 0.04307 -0.0884 0.9377 0.0737
-9.250 -0.5145 0.04946 0.04121 -0.0896 0.9249 0.0785
-9.000 -0.4972 0.04722 0.03870 -0.0906 0.9118 0.0845
-8.750 -0.4749 0.04552 0.03700 -0.0917 0.9000 0.0913
-8.500 -0.4487 0.04358 0.03499 -0.0934 0.8901 0.1000
-8.250 -0.4313 0.04191 0.03323 -0.0934 0.8767 0.1088
-8.000 -0.4114 0.04024 0.03145 -0.0938 0.8648 0.1197
-7.750 -0.3853 0.03841 0.02961 -0.0952 0.8557 0.1334
-7.500 -0.3691 0.03697 0.02817 -0.0949 0.8426 0.1471
-7.250 -0.3440 0.03526 0.02656 -0.0961 0.8334 0.1658
-7.000 -0.3248 0.03383 0.02524 -0.0963 0.8215 0.1874
-6.750 -0.3040 0.03255 0.02410 -0.0965 0.8103 0.2152
-6.500 -0.2741 0.03158 0.02338 -0.0976 0.8010 0.2546
-6.250 -0.2510 0.03139 0.02331 -0.0970 0.7889 0.2944
-6.000 -0.2122 0.03150 0.02336 -0.0983 0.7808 0.3362
-5.750 -0.1897 0.03181 0.02351 -0.0971 0.7681 0.3637
-5.500 -0.1491 0.03204 0.02350 -0.0985 0.7606 0.3903
-5.000 -0.0954 0.03247 0.02352 -0.0974 0.7392 0.4266
-4.750 -0.0731 0.03260 0.02344 -0.0964 0.7278 0.4434
-4.500 -0.0421 0.03292 0.02360 -0.0960 0.7191 0.4595
-4.250 -0.0179 0.03334 0.02395 -0.0944 0.7086 0.4718
-4.000 0.0116 0.03325 0.02362 -0.0946 0.7004 0.4859
-3.750 0.0323 0.03327 0.02351 -0.0934 0.6903 0.4966
-3.500 0.0666 0.03306 0.02307 -0.0942 0.6835 0.5073
-3.250 0.0811 0.03309 0.02300 -0.0923 0.6729 0.5166
-3.000 0.1139 0.03279 0.02247 -0.0932 0.6662 0.5259
-2.750 0.1300 0.03286 0.02247 -0.0914 0.6570 0.5332
-2.500 0.1583 0.03250 0.02187 -0.0922 0.6497 0.5426
-2.250 0.1833 0.03249 0.02176 -0.0915 0.6426 0.5486
-2.000 0.2024 0.03246 0.02162 -0.0906 0.6343 0.5557
-1.750 0.2352 0.03216 0.02110 -0.0919 0.6286 0.5635
-1.500 0.2511 0.03236 0.02127 -0.0901 0.6210 0.5689
-1.250 0.2742 0.03235 0.02113 -0.0898 0.6141 0.5758
-1.000 0.3087 0.03210 0.02067 -0.0913 0.6091 0.5831
-0.750 0.3201 0.03246 0.02105 -0.0889 0.6014 0.5883
-0.500 0.3431 0.03254 0.02103 -0.0885 0.5952 0.5953
-0.250 0.3767 0.03240 0.02070 -0.0898 0.5907 0.6026
0.000 0.3888 0.03285 0.02117 -0.0876 0.5842 0.6080
0.250 0.4053 0.03319 0.02147 -0.0863 0.5780 0.6149
0.500 0.4359 0.03318 0.02132 -0.0871 0.5734 0.6222
0.750 0.4634 0.03331 0.02136 -0.0872 0.5690 0.6288
1.000 0.4644 0.03419 0.02230 -0.0838 0.5617 0.6355
1.250 0.4871 0.03448 0.02253 -0.0834 0.5569 0.6428
1.500 0.5191 0.03452 0.02248 -0.0841 0.5534 0.6505
1.750 0.5287 0.03533 0.02327 -0.0822 0.5479 0.6586
2.000 0.5277 0.03637 0.02442 -0.0784 0.5415 0.6647
2.250 0.5521 0.03668 0.02467 -0.0782 0.5374 0.6739
2.500 0.5875 0.03665 0.02458 -0.0795 0.5344 0.6834
2.750 0.5643 0.03862 0.02668 -0.0732 0.5274 0.6904
3.000 0.5631 0.04012 0.02824 -0.0702 0.5216 0.6994
3.250 0.5876 0.04043 0.02855 -0.0699 0.5181 0.7104
3.500 0.6230 0.04028 0.02837 -0.0709 0.5157 0.7231
4.000 0.5768 0.04617 0.03454 -0.0618 0.5005 0.7434
4.250 0.6033 0.04636 0.03475 -0.0616 0.4981 0.7602
4.500 0.6359 0.04610 0.03454 -0.0618 0.4964 0.7811
5.000 0.5852 0.05391 0.04273 -0.0556 0.4796 0.8242
5.250 0.6215 0.05360 0.04259 -0.0566 0.4780 0.8977
5.750 0.5863 0.06272 0.05174 -0.0558 0.4614 1.0000
6.250 0.5661 0.07080 0.05979 -0.0556 0.4479 1.0000
6.500 0.5876 0.07204 0.06094 -0.0561 0.4450 1.0000
6.750 0.6150 0.07268 0.06149 -0.0564 0.4428 1.0000
7.000 0.5849 0.07845 0.06731 -0.0560 0.4341 1.0000
7.250 0.5942 0.08076 0.06959 -0.0562 0.4301 1.0000
7.500 0.6137 0.08214 0.07092 -0.0564 0.4272 1.0000
7.750 0.6398 0.08293 0.07166 -0.0566 0.4251 1.0000
8.000 0.6153 0.08821 0.07700 -0.0565 0.4171 1.0000
8.250 0.6222 0.09078 0.07957 -0.0567 0.4131 1.0000
8.500 0.6400 0.09233 0.08110 -0.0569 0.4101 1.0000
8.750 0.6638 0.09334 0.08208 -0.0569 0.4077 1.0000
9.000 0.6478 0.09791 0.08670 -0.0572 0.4008 1.0000
9.250 0.6521 0.10073 0.08956 -0.0575 0.3964 1.0000
9.500 0.6681 0.10246 0.09128 -0.0576 0.3931 1.0000
9.750 0.6917 0.10348 0.09229 -0.0577 0.3905 1.0000
10.000 0.6804 0.10768 0.09654 -0.0581 0.3842 1.0000
10.250 0.6838 0.11055 0.09947 -0.0585 0.3794 1.0000
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Polar data table (+)
Polar graphs
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