EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 858 AIRFOIL (e858-il) Reynolds number: 200,000 Max Cl/Cd: 48.72 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e858-il-200000.txt Download as CSV file: xf-e858-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6380 0.08927 0.08419 -0.0790 1.0000 0.0314
-16.000 -0.6640 0.08264 0.07733 -0.0823 1.0000 0.0313
-15.750 -0.6774 0.07812 0.07268 -0.0839 1.0000 0.0314
-15.500 -0.6754 0.07587 0.07045 -0.0841 1.0000 0.0318
-15.250 -0.6833 0.07239 0.06688 -0.0849 1.0000 0.0320
-15.000 -0.6861 0.06978 0.06425 -0.0852 1.0000 0.0326
-14.750 -0.6948 0.06658 0.06095 -0.0856 1.0000 0.0328
-14.500 -0.7023 0.06367 0.05794 -0.0857 1.0000 0.0331
-14.250 -0.7119 0.06079 0.05496 -0.0858 1.0000 0.0337
-14.000 -0.7203 0.05815 0.05221 -0.0855 1.0000 0.0340
-13.750 -0.7286 0.05567 0.04961 -0.0847 1.0000 0.0343
-13.500 -0.7404 0.05322 0.04701 -0.0839 1.0000 0.0347
-13.250 -0.7480 0.05132 0.04503 -0.0823 1.0000 0.0351
-13.000 -0.7428 0.05057 0.04441 -0.0800 1.0000 0.0357
-12.750 -0.7473 0.04947 0.04335 -0.0778 0.9999 0.0362
-12.500 -0.7169 0.04743 0.04125 -0.0821 0.9951 0.0375
-12.250 -0.6894 0.04519 0.03885 -0.0863 0.9898 0.0389
-12.000 -0.6563 0.04379 0.03754 -0.0891 0.9843 0.0406
-11.750 -0.6265 0.04187 0.03557 -0.0929 0.9788 0.0427
-11.500 -0.5988 0.04001 0.03372 -0.0959 0.9713 0.0449
-11.250 -0.5748 0.03803 0.03173 -0.0986 0.9615 0.0474
-11.000 -0.5544 0.03593 0.02965 -0.1010 0.9500 0.0504
-10.750 -0.5356 0.03373 0.02740 -0.1033 0.9374 0.0544
-10.500 -0.5165 0.03162 0.02532 -0.1056 0.9250 0.0582
-10.250 -0.4980 0.02931 0.02301 -0.1080 0.9135 0.0632
-10.000 -0.4812 0.02706 0.02073 -0.1102 0.9001 0.0685
-9.750 -0.4617 0.02515 0.01878 -0.1120 0.8845 0.0754
-9.500 -0.4288 0.02340 0.01697 -0.1154 0.8696 0.0859
-9.250 -0.3868 0.02164 0.01522 -0.1206 0.8545 0.0990
-9.000 -0.3357 0.02016 0.01371 -0.1272 0.8373 0.1167
-8.750 -0.2952 0.01909 0.01255 -0.1312 0.8165 0.1356
-8.500 -0.2687 0.01818 0.01163 -0.1325 0.7952 0.1540
-8.250 -0.2466 0.01751 0.01089 -0.1324 0.7753 0.1747
-8.000 -0.2280 0.01683 0.01022 -0.1316 0.7574 0.1986
-7.750 -0.2136 0.01629 0.00973 -0.1297 0.7401 0.2266
-7.500 -0.1969 0.01591 0.00943 -0.1281 0.7245 0.2605
-7.250 -0.1745 0.01579 0.00927 -0.1273 0.7104 0.2938
-7.000 -0.1533 0.01584 0.00929 -0.1259 0.6958 0.3180
-6.750 -0.1303 0.01599 0.00935 -0.1248 0.6825 0.3371
-6.500 -0.1045 0.01620 0.00940 -0.1241 0.6702 0.3529
-6.250 -0.0829 0.01638 0.00940 -0.1228 0.6579 0.3667
-6.000 -0.0547 0.01672 0.00969 -0.1224 0.6471 0.3770
-5.750 -0.0334 0.01685 0.00969 -0.1210 0.6356 0.3879
-5.500 -0.0052 0.01721 0.01000 -0.1206 0.6253 0.3963
-5.250 0.0167 0.01736 0.01003 -0.1193 0.6146 0.4059
-5.000 0.0433 0.01755 0.01015 -0.1187 0.6050 0.4129
-4.750 0.0682 0.01780 0.01036 -0.1178 0.5955 0.4202
-4.500 0.0918 0.01790 0.01025 -0.1169 0.5865 0.4285
-4.250 0.1198 0.01803 0.01035 -0.1167 0.5784 0.4342
-4.000 0.1434 0.01817 0.01050 -0.1155 0.5697 0.4402
-3.750 0.1693 0.01829 0.01044 -0.1151 0.5620 0.4475
-3.500 0.1942 0.01830 0.01035 -0.1145 0.5542 0.4535
-3.250 0.2182 0.01837 0.01046 -0.1135 0.5462 0.4585
-3.000 0.2456 0.01854 0.01050 -0.1132 0.5394 0.4646
-2.750 0.2701 0.01863 0.01048 -0.1126 0.5326 0.4714
-2.500 0.2939 0.01856 0.01036 -0.1118 0.5258 0.4767
-2.250 0.3206 0.01861 0.01036 -0.1114 0.5198 0.4810
-2.000 0.3482 0.01875 0.01041 -0.1114 0.5140 0.4858
-1.750 0.3712 0.01873 0.01036 -0.1105 0.5079 0.4907
-1.500 0.3964 0.01872 0.01022 -0.1100 0.5022 0.4954
-1.250 0.4247 0.01871 0.01007 -0.1102 0.4968 0.4996
-1.000 0.4491 0.01875 0.01013 -0.1096 0.4916 0.5034
-0.750 0.4728 0.01876 0.01015 -0.1088 0.4864 0.5072
-0.500 0.4985 0.01880 0.01012 -0.1084 0.4816 0.5117
-0.250 0.5268 0.01892 0.01009 -0.1086 0.4773 0.5169
0.000 0.5550 0.01908 0.01014 -0.1088 0.4731 0.5213
0.250 0.5769 0.01905 0.01019 -0.1077 0.4687 0.5250
0.500 0.6011 0.01910 0.01025 -0.1071 0.4643 0.5289
0.750 0.6270 0.01918 0.01028 -0.1067 0.4602 0.5334
1.000 0.6562 0.01937 0.01033 -0.1071 0.4564 0.5389
1.250 0.6834 0.01962 0.01050 -0.1072 0.4528 0.5438
1.500 0.7046 0.01964 0.01062 -0.1060 0.4492 0.5480
1.750 0.7280 0.01976 0.01078 -0.1053 0.4456 0.5524
2.000 0.7533 0.01990 0.01090 -0.1049 0.4422 0.5575
2.250 0.7805 0.02006 0.01099 -0.1049 0.4391 0.5631
2.500 0.8109 0.02031 0.01113 -0.1056 0.4359 0.5687
2.750 0.8351 0.02056 0.01145 -0.1051 0.4328 0.5740
3.000 0.8542 0.02072 0.01169 -0.1036 0.4297 0.5795
3.250 0.8762 0.02092 0.01191 -0.1026 0.4265 0.5855
3.500 0.9001 0.02111 0.01209 -0.1021 0.4236 0.5913
3.750 0.9254 0.02127 0.01229 -0.1018 0.4210 0.5973
4.000 0.9532 0.02152 0.01250 -0.1020 0.4185 0.6048
4.250 0.9858 0.02197 0.01285 -0.1032 0.4158 0.6129
4.500 1.0053 0.02226 0.01327 -0.1019 0.4134 0.6196
4.750 1.0208 0.02249 0.01363 -0.0998 0.4107 0.6272
5.000 1.0392 0.02277 0.01395 -0.0983 0.4079 0.6357
5.250 1.0591 0.02299 0.01428 -0.0971 0.4053 0.6444
5.500 1.0820 0.02327 0.01458 -0.0964 0.4029 0.6554
5.750 1.1070 0.02351 0.01487 -0.0961 0.4007 0.6664
6.250 1.1685 0.02440 0.01576 -0.0979 0.3962 0.6945
6.500 1.1797 0.02474 0.01628 -0.0952 0.3942 0.7099
6.750 1.1887 0.02507 0.01681 -0.0921 0.3919 0.7294
7.000 1.1967 0.02535 0.01730 -0.0888 0.3895 0.7544
7.250 1.2070 0.02563 0.01777 -0.0859 0.3873 0.7921
7.500 1.2359 0.02582 0.01831 -0.0864 0.3850 0.9123
7.750 1.2644 0.02625 0.01869 -0.0872 0.3829 1.0000
8.000 1.2922 0.02669 0.01905 -0.0878 0.3809 1.0000
8.250 1.3262 0.02722 0.01949 -0.0894 0.3790 1.0000
8.500 1.3509 0.02807 0.02031 -0.0896 0.3767 1.0000
8.750 1.3451 0.02873 0.02110 -0.0843 0.3749 1.0000
9.000 1.3431 0.02950 0.02199 -0.0799 0.3727 1.0000
9.250 1.3448 0.03035 0.02292 -0.0763 0.3705 1.0000
9.500 1.3491 0.03119 0.02383 -0.0733 0.3684 1.0000
9.750 1.3578 0.03198 0.02467 -0.0710 0.3664 1.0000
10.000 1.3715 0.03266 0.02537 -0.0694 0.3646 1.0000
10.250 1.3952 0.03312 0.02580 -0.0693 0.3628 1.0000
10.500 1.4298 0.03346 0.02608 -0.0708 0.3609 1.0000
10.750 1.4604 0.03438 0.02696 -0.0720 0.3589 1.0000
11.000 1.4187 0.03637 0.02920 -0.0632 0.3569 1.0000
11.250 1.3543 0.04004 0.03317 -0.0537 0.3540 1.0000
11.500 0.7177 0.11129 0.10556 -0.0459 0.3091 1.0000
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