EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 858 AIRFOIL (e858-il) Reynolds number: 100,000 Max Cl/Cd: 34.55 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e858-il-100000-n5.txt Download as CSV file: xf-e858-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 858 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.4582 0.11505 0.10911 -0.0623 1.0000 0.0346
-15.500 -0.5023 0.10320 0.09699 -0.0681 1.0000 0.0347
-15.250 -0.5300 0.09521 0.08876 -0.0718 1.0000 0.0350
-15.000 -0.5324 0.09201 0.08558 -0.0726 1.0000 0.0355
-14.750 -0.5384 0.08832 0.08186 -0.0736 1.0000 0.0361
-14.500 -0.5464 0.08443 0.07792 -0.0746 1.0000 0.0367
-14.250 -0.5549 0.08062 0.07402 -0.0755 1.0000 0.0374
-14.000 -0.5617 0.07724 0.07055 -0.0760 1.0000 0.0380
-13.750 -0.5700 0.07383 0.06701 -0.0764 1.0000 0.0389
-13.500 -0.5734 0.07133 0.06450 -0.0761 1.0000 0.0396
-13.250 -0.5766 0.06913 0.06233 -0.0756 1.0000 0.0403
-13.000 -0.5817 0.06691 0.06011 -0.0750 1.0000 0.0411
-12.750 -0.5885 0.06470 0.05789 -0.0741 1.0000 0.0421
-12.500 -0.5816 0.06203 0.05510 -0.0759 0.9973 0.0439
-12.250 -0.5618 0.05919 0.05229 -0.0805 0.9917 0.0460
-12.000 -0.5431 0.05635 0.04934 -0.0844 0.9846 0.0489
-11.750 -0.5255 0.05373 0.04673 -0.0878 0.9766 0.0514
-11.500 -0.5101 0.05127 0.04422 -0.0903 0.9653 0.0545
-11.250 -0.5005 0.04883 0.04179 -0.0918 0.9495 0.0573
-10.750 -0.4785 0.04415 0.03702 -0.0951 0.9177 0.0652
-10.500 -0.4671 0.04178 0.03467 -0.0969 0.9021 0.0692
-10.250 -0.4537 0.03942 0.03226 -0.0991 0.8866 0.0746
-10.000 -0.4375 0.03711 0.02990 -0.1015 0.8711 0.0807
-9.750 -0.4188 0.03477 0.02748 -0.1045 0.8556 0.0880
-9.500 -0.3987 0.03242 0.02504 -0.1080 0.8395 0.0964
-9.000 -0.3570 0.02852 0.02093 -0.1137 0.8038 0.1169
-8.750 -0.3359 0.02709 0.01941 -0.1152 0.7856 0.1293
-8.500 -0.3168 0.02589 0.01813 -0.1159 0.7683 0.1434
-8.250 -0.2966 0.02483 0.01698 -0.1164 0.7520 0.1599
-8.000 -0.2762 0.02386 0.01595 -0.1167 0.7367 0.1785
-7.750 -0.2613 0.02306 0.01518 -0.1156 0.7214 0.1983
-7.500 -0.2409 0.02238 0.01450 -0.1153 0.7079 0.2234
-7.250 -0.2196 0.02191 0.01408 -0.1148 0.6943 0.2510
-7.000 -0.1982 0.02167 0.01384 -0.1140 0.6814 0.2773
-6.750 -0.1717 0.02159 0.01366 -0.1139 0.6696 0.3017
-6.500 -0.1498 0.02159 0.01358 -0.1128 0.6573 0.3208
-6.000 -0.1002 0.02171 0.01342 -0.1116 0.6351 0.3519
-5.750 -0.0742 0.02173 0.01317 -0.1113 0.6254 0.3661
-5.500 -0.0503 0.02196 0.01340 -0.1102 0.6148 0.3753
-5.250 -0.0259 0.02192 0.01308 -0.1097 0.6054 0.3871
-5.000 -0.0005 0.02217 0.01332 -0.1088 0.5960 0.3944
-4.750 0.0232 0.02220 0.01317 -0.1080 0.5869 0.4041
-4.500 0.0496 0.02230 0.01312 -0.1076 0.5790 0.4116
-4.250 0.0730 0.02244 0.01323 -0.1065 0.5703 0.4187
-4.000 0.0972 0.02238 0.01292 -0.1060 0.5627 0.4278
-3.750 0.1227 0.02250 0.01299 -0.1053 0.5554 0.4335
-3.500 0.1461 0.02261 0.01306 -0.1043 0.5473 0.4398
-3.250 0.1709 0.02259 0.01285 -0.1038 0.5404 0.4475
-3.000 0.1955 0.02256 0.01268 -0.1033 0.5338 0.4534
-2.750 0.2190 0.02262 0.01274 -0.1024 0.5267 0.4577
-2.500 0.2441 0.02263 0.01265 -0.1018 0.5207 0.4625
-2.250 0.2707 0.02263 0.01244 -0.1017 0.5154 0.4680
-2.000 0.2932 0.02256 0.01225 -0.1010 0.5089 0.4736
-1.750 0.3171 0.02256 0.01223 -0.1002 0.5028 0.4770
-1.500 0.3428 0.02259 0.01216 -0.0998 0.4976 0.4806
-1.250 0.3675 0.02265 0.01215 -0.0992 0.4924 0.4850
-1.000 0.3903 0.02269 0.01214 -0.0984 0.4867 0.4899
-0.750 0.4147 0.02272 0.01204 -0.0980 0.4817 0.4949
-0.500 0.4408 0.02275 0.01196 -0.0977 0.4774 0.4988
-0.250 0.4669 0.02285 0.01200 -0.0975 0.4734 0.5025
0.000 0.4884 0.02297 0.01215 -0.0964 0.4685 0.5068
0.250 0.5114 0.02307 0.01222 -0.0956 0.4637 0.5118
0.500 0.5361 0.02316 0.01220 -0.0952 0.4594 0.5168
0.750 0.5629 0.02326 0.01215 -0.0952 0.4557 0.5213
1.000 0.5858 0.02341 0.01233 -0.0943 0.4518 0.5251
1.250 0.6068 0.02360 0.01256 -0.0932 0.4477 0.5297
1.500 0.6294 0.02378 0.01273 -0.0924 0.4439 0.5351
1.750 0.6536 0.02395 0.01283 -0.0919 0.4404 0.5408
2.000 0.6791 0.02410 0.01292 -0.0917 0.4373 0.5455
2.250 0.7070 0.02429 0.01303 -0.0918 0.4344 0.5501
2.500 0.7236 0.02456 0.01340 -0.0900 0.4307 0.5554
2.750 0.7428 0.02482 0.01369 -0.0887 0.4269 0.5614
3.000 0.7642 0.02507 0.01393 -0.0878 0.4235 0.5676
3.250 0.7866 0.02529 0.01417 -0.0870 0.4206 0.5730
3.500 0.8112 0.02552 0.01437 -0.0866 0.4180 0.5792
3.750 0.8391 0.02578 0.01456 -0.0869 0.4157 0.5864
4.000 0.8556 0.02613 0.01499 -0.0851 0.4129 0.5928
4.250 0.8674 0.02650 0.01548 -0.0826 0.4098 0.5993
4.500 0.8819 0.02687 0.01591 -0.0806 0.4067 0.6074
4.750 0.8997 0.02722 0.01629 -0.0791 0.4038 0.6153
5.000 0.9207 0.02753 0.01663 -0.0782 0.4012 0.6234
5.250 0.9452 0.02784 0.01691 -0.0779 0.3988 0.6334
5.500 0.9723 0.02814 0.01721 -0.0781 0.3969 0.6435
5.750 0.9892 0.02866 0.01779 -0.0766 0.3947 0.6554
6.000 0.9937 0.02936 0.01868 -0.0733 0.3920 0.6663
6.250 1.0012 0.03005 0.01951 -0.0705 0.3892 0.6800
6.500 1.0114 0.03065 0.02024 -0.0682 0.3865 0.6949
6.750 1.0260 0.03114 0.02082 -0.0665 0.3839 0.7133
7.000 1.0445 0.03151 0.02130 -0.0653 0.3817 0.7377
7.250 1.0665 0.03177 0.02166 -0.0646 0.3798 0.7728
7.500 1.0949 0.03189 0.02196 -0.0649 0.3781 0.8455
7.750 1.1078 0.03271 0.02294 -0.0637 0.3759 1.0000
8.000 1.0923 0.03440 0.02479 -0.0589 0.3731 1.0000
8.250 1.0793 0.03623 0.02674 -0.0548 0.3700 1.0000
8.500 1.0735 0.03792 0.02850 -0.0519 0.3671 1.0000
8.750 1.0799 0.03914 0.02973 -0.0503 0.3645 1.0000
9.000 1.0974 0.03990 0.03045 -0.0497 0.3626 1.0000
9.250 1.1224 0.04033 0.03083 -0.0498 0.3610 1.0000
9.500 1.1530 0.04057 0.03100 -0.0504 0.3596 1.0000
10.000 0.9091 0.06438 0.05558 -0.0388 0.3408 1.0000
10.250 0.9555 0.06215 0.05327 -0.0388 0.3415 1.0000
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