EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 100,000 Max Cl/Cd: 52.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e561-il-100000-n5.txt Download as CSV file: xf-e561-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 561 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4001 0.10373 0.09833 -0.0580 1.0000 0.0343
-12.500 -0.4621 0.08811 0.08252 -0.0656 1.0000 0.0339
-12.250 -0.4911 0.08044 0.07472 -0.0690 1.0000 0.0337
-12.000 -0.5143 0.07455 0.06874 -0.0712 1.0000 0.0337
-11.750 -0.5324 0.06997 0.06408 -0.0724 1.0000 0.0338
-11.500 -0.5490 0.06606 0.06011 -0.0730 1.0000 0.0339
-11.250 -0.5660 0.06260 0.05660 -0.0729 1.0000 0.0341
-11.000 -0.5822 0.05979 0.05377 -0.0720 1.0000 0.0342
-10.750 -0.5987 0.05697 0.05092 -0.0714 0.9993 0.0343
-10.500 -0.5834 0.05324 0.04702 -0.0770 0.9919 0.0351
-10.250 -0.5659 0.05040 0.04418 -0.0815 0.9837 0.0359
-10.000 -0.5542 0.04729 0.04100 -0.0858 0.9725 0.0367
-9.750 -0.5419 0.04383 0.03743 -0.0906 0.9599 0.0379
-9.500 -0.5251 0.04034 0.03378 -0.0960 0.9472 0.0392
-9.250 -0.5056 0.03686 0.03014 -0.1017 0.9345 0.0411
-9.000 -0.4847 0.03414 0.02731 -0.1058 0.9227 0.0434
-8.750 -0.4584 0.03176 0.02478 -0.1097 0.9134 0.0475
-8.500 -0.4299 0.02955 0.02244 -0.1133 0.9044 0.0531
-8.250 -0.4024 0.02753 0.02033 -0.1162 0.8945 0.0612
-8.000 -0.3682 0.02556 0.01834 -0.1200 0.8872 0.0744
-7.750 -0.3372 0.02419 0.01690 -0.1224 0.8771 0.0926
-7.500 -0.2983 0.02302 0.01568 -0.1257 0.8700 0.1138
-7.250 -0.2646 0.02225 0.01488 -0.1278 0.8596 0.1343
-7.000 -0.2229 0.02164 0.01416 -0.1311 0.8520 0.1601
-6.750 -0.1895 0.02132 0.01378 -0.1326 0.8405 0.1781
-6.500 -0.1499 0.02090 0.01319 -0.1350 0.8316 0.1927
-6.250 -0.1153 0.02054 0.01262 -0.1365 0.8199 0.2057
-6.000 -0.0812 0.02032 0.01234 -0.1377 0.8086 0.2167
-5.750 -0.0433 0.02003 0.01189 -0.1396 0.7985 0.2279
-5.500 -0.0126 0.01977 0.01143 -0.1402 0.7855 0.2390
-5.250 0.0194 0.01963 0.01122 -0.1409 0.7740 0.2479
-5.000 0.0538 0.01939 0.01079 -0.1421 0.7633 0.2580
-4.750 0.0826 0.01928 0.01058 -0.1422 0.7508 0.2669
-4.500 0.1135 0.01911 0.01028 -0.1428 0.7397 0.2758
-4.250 0.1445 0.01900 0.01002 -0.1433 0.7289 0.2850
-4.000 0.1725 0.01890 0.00982 -0.1433 0.7174 0.2933
-3.750 0.2029 0.01882 0.00960 -0.1436 0.7075 0.3023
-3.500 0.2309 0.01874 0.00943 -0.1436 0.6966 0.3105
-3.250 0.2595 0.01869 0.00928 -0.1437 0.6867 0.3191
-3.000 0.2883 0.01863 0.00909 -0.1437 0.6769 0.3275
-2.750 0.3157 0.01861 0.00901 -0.1436 0.6672 0.3359
-2.500 0.3447 0.01857 0.00882 -0.1437 0.6585 0.3445
-2.250 0.3716 0.01857 0.00879 -0.1435 0.6490 0.3526
-2.000 0.4004 0.01855 0.00863 -0.1436 0.6406 0.3618
-1.750 0.4269 0.01857 0.00864 -0.1433 0.6316 0.3695
-1.500 0.4555 0.01858 0.00851 -0.1433 0.6238 0.3792
-1.250 0.4822 0.01862 0.00855 -0.1430 0.6157 0.3870
-1.000 0.5100 0.01866 0.00847 -0.1430 0.6078 0.3970
-0.750 0.5371 0.01870 0.00850 -0.1428 0.6005 0.4050
-0.500 0.5640 0.01877 0.00850 -0.1426 0.5926 0.4152
-0.250 0.5922 0.01882 0.00851 -0.1425 0.5865 0.4236
0.000 0.6181 0.01892 0.00859 -0.1422 0.5787 0.4340
0.250 0.6448 0.01898 0.00866 -0.1419 0.5720 0.4429
0.500 0.6720 0.01909 0.00870 -0.1417 0.5657 0.4534
0.750 0.6976 0.01919 0.00885 -0.1413 0.5587 0.4633
1.000 0.7252 0.01930 0.00891 -0.1412 0.5531 0.4741
1.250 0.7514 0.01944 0.00906 -0.1409 0.5469 0.4856
1.500 0.7770 0.01957 0.00923 -0.1405 0.5405 0.4968
1.750 0.8045 0.01969 0.00932 -0.1404 0.5353 0.5095
2.000 0.8299 0.01986 0.00953 -0.1399 0.5295 0.5228
2.250 0.8552 0.02002 0.00976 -0.1395 0.5237 0.5364
2.500 0.8822 0.02017 0.00990 -0.1393 0.5186 0.5516
2.750 0.9078 0.02036 0.01013 -0.1389 0.5133 0.5683
3.000 0.9322 0.02056 0.01043 -0.1383 0.5076 0.5869
3.250 0.9582 0.02072 0.01064 -0.1379 0.5028 0.6082
3.500 0.9849 0.02090 0.01083 -0.1376 0.4985 0.6333
3.750 1.0065 0.02111 0.01124 -0.1365 0.4927 0.6616
4.000 1.0296 0.02127 0.01153 -0.1355 0.4877 0.6970
4.250 1.0529 0.02137 0.01173 -0.1345 0.4837 0.7433
4.750 1.0868 0.02147 0.01224 -0.1298 0.4740 1.0000
5.000 1.1136 0.02182 0.01253 -0.1299 0.4693 1.0000
5.250 1.1424 0.02214 0.01275 -0.1302 0.4654 1.0000
5.500 1.1643 0.02261 0.01328 -0.1294 0.4603 1.0000
5.750 1.1876 0.02303 0.01371 -0.1289 0.4552 1.0000
6.000 1.2136 0.02339 0.01404 -0.1287 0.4509 1.0000
6.250 1.2404 0.02377 0.01437 -0.1287 0.4470 1.0000
6.500 1.2589 0.02431 0.01502 -0.1274 0.4417 1.0000
6.750 1.2814 0.02475 0.01550 -0.1267 0.4369 1.0000
7.000 1.3073 0.02511 0.01583 -0.1265 0.4329 1.0000
7.250 1.3292 0.02561 0.01636 -0.1257 0.4286 1.0000
7.500 1.3462 0.02620 0.01707 -0.1242 0.4234 1.0000
7.750 1.3679 0.02665 0.01755 -0.1233 0.4188 1.0000
8.000 1.3943 0.02701 0.01788 -0.1232 0.4150 1.0000
8.250 1.4088 0.02768 0.01868 -0.1214 0.4101 1.0000
8.500 1.4239 0.02831 0.01942 -0.1196 0.4049 1.0000
8.750 1.4454 0.02875 0.01988 -0.1187 0.4006 1.0000
9.000 1.4696 0.02916 0.02028 -0.1183 0.3966 1.0000
9.250 1.4727 0.03003 0.02136 -0.1148 0.3912 1.0000
9.500 1.4863 0.03066 0.02207 -0.1128 0.3863 1.0000
9.750 1.5090 0.03104 0.02244 -0.1122 0.3821 1.0000
10.000 1.5158 0.03191 0.02345 -0.1094 0.3772 1.0000
10.250 1.5203 0.03288 0.02457 -0.1064 0.3719 1.0000
10.500 1.5368 0.03342 0.02515 -0.1050 0.3671 1.0000
10.750 1.5506 0.03411 0.02589 -0.1034 0.3625 1.0000
11.000 1.5455 0.03560 0.02758 -0.0997 0.3568 1.0000
11.250 1.5563 0.03641 0.02845 -0.0979 0.3515 1.0000
11.500 1.5705 0.03710 0.02919 -0.0965 0.3467 1.0000
11.750 1.5580 0.03928 0.03158 -0.0929 0.3406 1.0000
12.000 1.5663 0.04033 0.03269 -0.0912 0.3350 1.0000
12.250 1.5717 0.04166 0.03410 -0.0895 0.3297 1.0000
12.500 1.5566 0.04455 0.03719 -0.0868 0.3232 1.0000
12.750 1.5687 0.04548 0.03815 -0.0857 0.3177 1.0000
13.000 1.5539 0.04876 0.04160 -0.0838 0.3114 1.0000
13.250 1.5451 0.05173 0.04471 -0.0825 0.3049 1.0000
13.500 1.5578 0.05274 0.04573 -0.0817 0.2993 1.0000
13.750 1.5216 0.05896 0.05219 -0.0807 0.2916 1.0000
14.000 1.5381 0.05959 0.05282 -0.0801 0.2859 1.0000
14.250 1.4971 0.06720 0.06065 -0.0803 0.2778 1.0000
14.500 1.5057 0.06885 0.06234 -0.0799 0.2714 1.0000
14.750 1.4703 0.07658 0.07024 -0.0809 0.2630 1.0000
15.000 1.4779 0.07849 0.07219 -0.0808 0.2564 1.0000
15.250 1.4443 0.08662 0.08047 -0.0826 0.2476 1.0000
15.500 1.4572 0.08780 0.08168 -0.0823 0.2412 1.0000
15.750 1.4252 0.09614 0.09016 -0.0846 0.2321 1.0000
16.000 1.4432 0.09651 0.09055 -0.0842 0.2259 1.0000
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