EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 100,000 Max Cl/Cd: 52.87 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e556-il-100000.txt Download as CSV file: xf-e556-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 556 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4786 0.10274 0.09763 -0.0591 1.0000 0.0593
-12.000 -0.4701 0.09980 0.09469 -0.0582 1.0000 0.0572
-11.750 -0.4839 0.09306 0.08798 -0.0606 1.0000 0.0555
-11.500 -0.5248 0.08276 0.07765 -0.0665 1.0000 0.0529
-11.250 -0.6032 0.07144 0.06610 -0.0741 1.0000 0.0500
-11.000 -0.6581 0.06716 0.06158 -0.0755 1.0000 0.0490
-10.750 -0.6885 0.06562 0.05995 -0.0733 1.0000 0.0486
-10.500 -0.7035 0.06303 0.05731 -0.0710 1.0000 0.0481
-10.250 -0.7176 0.05981 0.05402 -0.0693 1.0000 0.0478
-10.000 -0.7311 0.05690 0.05101 -0.0671 1.0000 0.0474
-9.750 -0.7422 0.05409 0.04805 -0.0650 1.0000 0.0470
-9.500 -0.7512 0.05119 0.04495 -0.0630 1.0000 0.0467
-9.250 -0.7554 0.04834 0.04186 -0.0612 1.0000 0.0465
-9.000 -0.7554 0.04551 0.03874 -0.0596 1.0000 0.0465
-8.750 -0.7506 0.04285 0.03576 -0.0582 1.0000 0.0466
-8.500 -0.7427 0.04057 0.03311 -0.0570 1.0000 0.0476
-8.250 -0.7315 0.03833 0.03054 -0.0560 1.0000 0.0489
-8.000 -0.7179 0.03629 0.02854 -0.0549 1.0000 0.0513
-7.750 -0.7028 0.03477 0.02694 -0.0538 1.0000 0.0540
-7.500 -0.6865 0.03319 0.02519 -0.0524 1.0000 0.0564
-7.250 -0.6702 0.03155 0.02342 -0.0509 1.0000 0.0597
-7.000 -0.6549 0.03033 0.02234 -0.0498 1.0000 0.0656
-6.750 -0.6388 0.02903 0.02104 -0.0485 1.0000 0.0727
-6.500 -0.6188 0.02793 0.01997 -0.0482 0.9993 0.0837
-6.250 -0.5794 0.02647 0.01878 -0.0519 0.9937 0.1086
-6.000 -0.5377 0.02360 0.01654 -0.0580 0.9882 0.1749
-5.750 -0.4926 0.02359 0.01782 -0.0628 0.9814 0.4165
-5.500 -0.4541 0.02583 0.01996 -0.0631 0.9730 0.4491
-5.250 -0.4189 0.02731 0.02128 -0.0636 0.9638 0.4735
-5.000 -0.3889 0.02888 0.02282 -0.0624 0.9546 0.4900
-4.750 -0.3517 0.03029 0.02416 -0.0625 0.9475 0.5059
-4.500 -0.3294 0.03180 0.02575 -0.0588 0.9375 0.5137
-4.250 -0.2988 0.03250 0.02636 -0.0583 0.9292 0.5266
-4.000 -0.2647 0.03301 0.02676 -0.0587 0.9215 0.5406
-3.750 -0.2353 0.03327 0.02690 -0.0588 0.9125 0.5537
-3.500 -0.2037 0.03380 0.02742 -0.0575 0.9057 0.5606
-3.250 -0.1685 0.03294 0.02633 -0.0611 0.8967 0.5712
-3.000 -0.1337 0.03290 0.02625 -0.0614 0.8903 0.5758
-2.750 -0.1028 0.03241 0.02564 -0.0630 0.8813 0.5819
-2.500 -0.0572 0.03147 0.02451 -0.0678 0.8752 0.5885
-2.250 -0.0277 0.03121 0.02420 -0.0682 0.8668 0.5923
-2.000 0.0135 0.03058 0.02344 -0.0713 0.8601 0.5978
-1.750 0.0706 0.02945 0.02212 -0.0781 0.8571 0.6037
-1.500 0.0908 0.02933 0.02198 -0.0768 0.8456 0.6069
-1.250 0.1412 0.02862 0.02120 -0.0808 0.8423 0.6119
-1.000 0.1728 0.02814 0.02062 -0.0829 0.8319 0.6167
-0.750 0.2237 0.02739 0.01979 -0.0872 0.8277 0.6212
-0.500 0.2535 0.02716 0.01955 -0.0876 0.8186 0.6252
-0.250 0.2995 0.02649 0.01881 -0.0912 0.8127 0.6303
0.000 0.3443 0.02585 0.01807 -0.0950 0.8059 0.6355
0.250 0.3753 0.02556 0.01781 -0.0953 0.7971 0.6392
0.500 0.4108 0.02524 0.01747 -0.0967 0.7891 0.6441
0.750 0.4522 0.02473 0.01688 -0.0997 0.7807 0.6499
1.000 0.4811 0.02455 0.01672 -0.0999 0.7711 0.6537
1.250 0.5193 0.02415 0.01631 -0.1014 0.7636 0.6585
1.500 0.5475 0.02409 0.01624 -0.1020 0.7527 0.6645
1.750 0.5904 0.02358 0.01570 -0.1044 0.7461 0.6697
2.000 0.6117 0.02366 0.01584 -0.1034 0.7342 0.6741
2.250 0.6438 0.02354 0.01570 -0.1044 0.7244 0.6801
2.500 0.6791 0.02327 0.01543 -0.1055 0.7156 0.6858
2.750 0.7016 0.02338 0.01561 -0.1046 0.7042 0.6914
3.000 0.7378 0.02321 0.01541 -0.1063 0.6948 0.6986
3.250 0.7650 0.02314 0.01539 -0.1059 0.6846 0.7035
3.500 0.7896 0.02325 0.01555 -0.1054 0.6732 0.7102
3.750 0.8224 0.02312 0.01544 -0.1062 0.6637 0.7173
4.000 0.8494 0.02310 0.01547 -0.1058 0.6528 0.7245
4.250 0.8743 0.02323 0.01565 -0.1055 0.6409 0.7320
4.500 0.9016 0.02321 0.01569 -0.1051 0.6304 0.7392
4.750 0.9339 0.02309 0.01556 -0.1057 0.6198 0.7481
5.000 0.9548 0.02324 0.01583 -0.1043 0.6073 0.7567
5.250 0.9794 0.02333 0.01600 -0.1037 0.5954 0.7659
5.500 1.0090 0.02330 0.01599 -0.1038 0.5842 0.7767
5.750 1.0346 0.02325 0.01599 -0.1030 0.5726 0.7869
6.000 1.0554 0.02340 0.01626 -0.1016 0.5596 0.7986
6.250 1.0778 0.02349 0.01645 -0.1005 0.5469 0.8119
6.500 1.1012 0.02351 0.01653 -0.0994 0.5343 0.8266
6.750 1.1248 0.02345 0.01650 -0.0982 0.5219 0.8431
7.000 1.1454 0.02338 0.01650 -0.0965 0.5090 0.8631
7.250 1.1585 0.02338 0.01665 -0.0935 0.4954 0.8890
7.500 1.1703 0.02324 0.01668 -0.0902 0.4821 0.9344
7.750 1.2066 0.02335 0.01680 -0.0924 0.4648 1.0000
8.000 1.2400 0.02363 0.01703 -0.0942 0.4472 1.0000
8.250 1.2674 0.02397 0.01730 -0.0945 0.4293 1.0000
8.500 1.2868 0.02441 0.01777 -0.0935 0.4107 1.0000
8.750 1.3044 0.02484 0.01821 -0.0920 0.3916 1.0000
9.000 1.3208 0.02530 0.01865 -0.0902 0.3723 1.0000
9.250 1.3362 0.02582 0.01907 -0.0883 0.3531 1.0000
9.500 1.3458 0.02649 0.01975 -0.0855 0.3332 1.0000
9.750 1.3523 0.02721 0.02047 -0.0823 0.3135 1.0000
10.000 1.3574 0.02802 0.02122 -0.0789 0.2946 1.0000
10.250 1.3627 0.02898 0.02206 -0.0758 0.2762 1.0000
10.500 1.3648 0.03012 0.02319 -0.0725 0.2580 1.0000
10.750 1.3665 0.03140 0.02444 -0.0693 0.2405 1.0000
11.000 1.3681 0.03282 0.02583 -0.0664 0.2239 1.0000
11.250 1.3696 0.03439 0.02735 -0.0637 0.2083 1.0000
11.500 1.3713 0.03610 0.02902 -0.0613 0.1937 1.0000
11.750 1.3729 0.03793 0.03081 -0.0592 0.1801 1.0000
12.000 1.3753 0.03986 0.03270 -0.0572 0.1675 1.0000
12.250 1.3787 0.04186 0.03461 -0.0555 0.1557 1.0000
12.500 1.3805 0.04395 0.03672 -0.0539 0.1450 1.0000
12.750 1.3812 0.04627 0.03916 -0.0524 0.1351 1.0000
13.000 1.3849 0.04857 0.04145 -0.0512 0.1258 1.0000
13.250 1.3897 0.05077 0.04357 -0.0501 0.1172 1.0000
13.500 1.3893 0.05352 0.04652 -0.0490 0.1100 1.0000
13.750 1.3995 0.05569 0.04854 -0.0483 0.1020 1.0000
14.000 1.3941 0.05881 0.05196 -0.0474 0.0968 1.0000
14.250 1.4089 0.06090 0.05385 -0.0469 0.0896 1.0000
14.500 1.3993 0.06450 0.05781 -0.0463 0.0859 1.0000
14.750 1.3994 0.06745 0.06087 -0.0459 0.0814 1.0000
15.000 1.4094 0.07020 0.06361 -0.0455 0.0765 1.0000
15.250 1.3985 0.07436 0.06809 -0.0456 0.0739 1.0000
15.500 1.3919 0.07825 0.07219 -0.0459 0.0710 1.0000
15.750 1.4121 0.08037 0.07411 -0.0454 0.0662 1.0000
16.000 1.3935 0.08553 0.07963 -0.0463 0.0651 1.0000
16.250 1.3749 0.09113 0.08556 -0.0478 0.0640 1.0000
16.500 1.3560 0.09714 0.09188 -0.0498 0.0628 1.0000
16.750 1.3366 0.10357 0.09858 -0.0524 0.0619 1.0000
17.000 1.3147 0.11072 0.10599 -0.0558 0.0612 1.0000
17.250 1.2845 0.11972 0.11529 -0.0608 0.0614 1.0000
17.500 1.2416 0.13195 0.12784 -0.0684 0.0630 1.0000
17.750 1.1966 0.14597 0.14206 -0.0777 0.0648 1.0000
18.000 1.1544 0.16100 0.15719 -0.0875 0.0662 1.0000
18.250 1.0493 0.20515 0.20119 -0.1131 0.0778 1.0000
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Polar data table (+)
Polar graphs
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