E205 (10.48%) (e205-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 100,000 Max Cl/Cd: 53.89 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e205-il-100000.txt Download as CSV file: xf-e205-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3871 0.09654 0.09179 -0.0246 1.0000 0.1066
-8.500 -0.3956 0.09377 0.08912 -0.0278 1.0000 0.1106
-8.250 -0.4156 0.09121 0.08671 -0.0327 1.0000 0.1118
-8.000 -0.3970 0.08662 0.08212 -0.0298 1.0000 0.1152
-7.750 -0.3893 0.08372 0.07926 -0.0289 1.0000 0.1193
-7.500 -0.4003 0.08095 0.07660 -0.0305 1.0000 0.1234
-7.250 -0.4341 0.07696 0.07264 -0.0397 1.0000 0.1271
-7.000 -0.4101 0.07374 0.06954 -0.0336 1.0000 0.1301
-6.750 -0.4063 0.07108 0.06692 -0.0327 1.0000 0.1346
-6.500 -0.4283 0.06738 0.06316 -0.0374 1.0000 0.1420
-6.250 -0.4181 0.06471 0.06063 -0.0334 1.0000 0.1447
-6.000 -0.4202 0.06275 0.05873 -0.0309 1.0000 0.1490
-5.750 -0.4461 0.06092 0.05678 -0.0302 1.0000 0.1567
-5.500 -0.4444 0.05887 0.05487 -0.0272 0.9988 0.1589
-5.250 -0.4059 0.05423 0.05008 -0.0338 0.9881 0.1741
-5.000 -0.3625 0.03622 0.03002 -0.0447 0.9761 0.0739
-4.750 -0.3218 0.03191 0.02498 -0.0477 0.9657 0.0676
-4.500 -0.2771 0.02875 0.02113 -0.0511 0.9571 0.0688
-4.250 -0.2371 0.02602 0.01790 -0.0533 0.9457 0.0687
-4.000 -0.1939 0.02382 0.01524 -0.0557 0.9356 0.0698
-3.750 -0.1467 0.02151 0.01277 -0.0590 0.9286 0.0737
-3.500 -0.1077 0.02034 0.01148 -0.0607 0.9166 0.0840
-3.250 -0.0724 0.01875 0.01007 -0.0619 0.9048 0.1018
-3.000 -0.0417 0.01699 0.00880 -0.0621 0.8928 0.1870
-2.750 -0.0150 0.01556 0.00833 -0.0621 0.8811 0.3706
-2.500 0.0085 0.01420 0.00814 -0.0602 0.8699 0.6391
-2.250 0.1022 0.01365 0.00798 -0.0694 0.8645 0.9451
-2.000 0.1945 0.01337 0.00719 -0.0816 0.8562 1.0000
-1.750 0.2157 0.01338 0.00694 -0.0805 0.8409 1.0000
-1.500 0.2366 0.01346 0.00679 -0.0793 0.8265 1.0000
-1.250 0.2576 0.01359 0.00671 -0.0781 0.8129 1.0000
-1.000 0.2791 0.01375 0.00667 -0.0770 0.8003 1.0000
-0.750 0.3009 0.01393 0.00668 -0.0759 0.7886 1.0000
-0.500 0.3235 0.01411 0.00668 -0.0748 0.7782 1.0000
-0.250 0.3462 0.01431 0.00673 -0.0738 0.7679 1.0000
0.000 0.3684 0.01456 0.00687 -0.0728 0.7571 1.0000
0.250 0.3915 0.01480 0.00698 -0.0718 0.7478 1.0000
0.500 0.4148 0.01503 0.00709 -0.0709 0.7387 1.0000
0.750 0.4374 0.01534 0.00734 -0.0700 0.7289 1.0000
1.000 0.4616 0.01558 0.00745 -0.0692 0.7212 1.0000
1.250 0.4841 0.01591 0.00775 -0.0683 0.7116 1.0000
1.500 0.5076 0.01623 0.00801 -0.0675 0.7033 1.0000
1.750 0.5313 0.01652 0.00825 -0.0667 0.6951 1.0000
2.000 0.5541 0.01691 0.00862 -0.0659 0.6865 1.0000
2.250 0.5787 0.01718 0.00883 -0.0650 0.6792 1.0000
2.500 0.6008 0.01763 0.00932 -0.0642 0.6703 1.0000
2.750 0.6261 0.01788 0.00951 -0.0635 0.6637 1.0000
3.000 0.6476 0.01838 0.01006 -0.0626 0.6544 1.0000
3.250 0.6728 0.01866 0.01030 -0.0619 0.6477 1.0000
3.500 0.6945 0.01914 0.01088 -0.0610 0.6384 1.0000
3.750 0.7183 0.01951 0.01126 -0.0602 0.6308 1.0000
4.000 0.7418 0.01987 0.01166 -0.0593 0.6222 1.0000
4.250 0.7642 0.02032 0.01217 -0.0584 0.6132 1.0000
4.500 0.7901 0.02050 0.01236 -0.0576 0.6055 1.0000
4.750 0.8113 0.02097 0.01295 -0.0566 0.5950 1.0000
5.000 0.8353 0.02125 0.01327 -0.0556 0.5859 1.0000
5.250 0.8608 0.02137 0.01342 -0.0548 0.5766 1.0000
5.500 0.8826 0.02172 0.01391 -0.0536 0.5653 1.0000
5.750 0.9061 0.02192 0.01418 -0.0526 0.5544 1.0000
6.000 0.9322 0.02190 0.01420 -0.0516 0.5439 1.0000
6.250 0.9573 0.02187 0.01422 -0.0506 0.5321 1.0000
6.500 0.9803 0.02192 0.01440 -0.0494 0.5187 1.0000
6.750 1.0038 0.02188 0.01445 -0.0481 0.5047 1.0000
7.000 1.0277 0.02175 0.01440 -0.0469 0.4898 1.0000
7.250 1.0519 0.02152 0.01422 -0.0456 0.4739 1.0000
7.500 1.0724 0.02143 0.01431 -0.0439 0.4549 1.0000
7.750 1.0935 0.02121 0.01419 -0.0422 0.4339 1.0000
8.000 1.1126 0.02106 0.01415 -0.0402 0.4093 1.0000
8.250 1.1297 0.02103 0.01420 -0.0380 0.3796 1.0000
8.500 1.1436 0.02122 0.01437 -0.0354 0.3420 1.0000
8.750 1.1524 0.02187 0.01492 -0.0324 0.2937 1.0000
9.000 1.1552 0.02313 0.01585 -0.0288 0.2433 1.0000
9.250 1.1543 0.02478 0.01718 -0.0252 0.1999 1.0000
9.500 1.1517 0.02651 0.01865 -0.0216 0.1652 1.0000
9.750 1.1471 0.02819 0.02016 -0.0179 0.1386 1.0000
10.000 1.1414 0.03007 0.02191 -0.0143 0.1168 1.0000
10.250 1.1347 0.03225 0.02397 -0.0113 0.0982 1.0000
10.500 1.1274 0.03484 0.02640 -0.0086 0.0820 1.0000
10.750 1.1241 0.03746 0.02897 -0.0064 0.0681 1.0000
11.000 1.1234 0.04002 0.03144 -0.0047 0.0579 1.0000
11.250 1.1318 0.04211 0.03361 -0.0032 0.0518 1.0000
11.500 1.1507 0.04450 0.03596 -0.0016 0.0468 1.0000
11.750 1.1691 0.04680 0.03849 -0.0003 0.0441 1.0000
12.000 1.1835 0.04934 0.04122 0.0008 0.0420 1.0000
12.250 1.1931 0.05185 0.04377 0.0016 0.0394 1.0000
12.500 1.2071 0.05605 0.04812 0.0023 0.0377 1.0000
12.750 1.2014 0.05906 0.05146 0.0034 0.0372 1.0000
13.000 1.1949 0.06254 0.05525 0.0041 0.0369 1.0000
13.250 1.1848 0.06650 0.05951 0.0044 0.0367 1.0000
13.500 1.1739 0.07081 0.06409 0.0043 0.0368 1.0000
13.750 1.1592 0.07550 0.06904 0.0036 0.0368 1.0000
14.000 1.1423 0.08067 0.07446 0.0022 0.0369 1.0000
14.250 1.1252 0.08615 0.08015 0.0004 0.0371 1.0000
14.500 1.1057 0.09220 0.08641 -0.0021 0.0373 1.0000
14.750 1.0865 0.09859 0.09298 -0.0050 0.0375 1.0000
15.000 1.0662 0.10561 0.10016 -0.0085 0.0377 1.0000
15.250 1.0466 0.11286 0.10759 -0.0125 0.0380 1.0000
15.500 0.7802 0.13317 0.12881 -0.0270 0.0495 1.0000
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Polar data table (+)
Polar graphs
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