EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 200,000 Max Cl/Cd: 77.49 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e851-il-200000.txt Download as CSV file: xf-e851-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3907 0.08745 0.08426 -0.0382 1.0000 0.0331
-8.750 -0.3965 0.08409 0.08095 -0.0377 1.0000 0.0336
-8.500 -0.4042 0.08080 0.07771 -0.0371 1.0000 0.0341
-8.250 -0.4143 0.07752 0.07449 -0.0363 1.0000 0.0345
-8.000 -0.5190 0.08168 0.07841 -0.0453 1.0000 0.0298
-7.750 -0.5348 0.07895 0.07565 -0.0446 1.0000 0.0299
-7.250 -0.5648 0.06912 0.06588 -0.0430 1.0000 0.0309
-7.000 -0.5688 0.06594 0.06272 -0.0417 1.0000 0.0315
-6.750 -0.5715 0.06282 0.05957 -0.0409 1.0000 0.0321
-6.500 -0.5713 0.05970 0.05638 -0.0405 1.0000 0.0329
-6.250 -0.5686 0.05625 0.05282 -0.0406 1.0000 0.0339
-6.000 -0.5624 0.05258 0.04898 -0.0409 1.0000 0.0352
-5.750 -0.5453 0.04836 0.04446 -0.0430 0.9988 0.0374
-5.500 -0.5146 0.04315 0.03839 -0.0478 0.9954 0.0431
-5.000 -0.4617 0.03556 0.03049 -0.0516 0.9910 0.0477
-4.750 -0.4223 0.02847 0.02235 -0.0502 0.9902 0.0161
-4.500 -0.3921 0.02501 0.01837 -0.0510 0.9886 0.0148
-4.250 -0.3607 0.02242 0.01535 -0.0515 0.9870 0.0141
-4.000 -0.3287 0.02040 0.01294 -0.0519 0.9852 0.0140
-3.750 -0.2963 0.01877 0.01113 -0.0526 0.9835 0.0150
-3.500 -0.2627 0.01771 0.00992 -0.0538 0.9819 0.0171
-3.250 -0.2296 0.01579 0.00819 -0.0554 0.9805 0.0794
-3.000 -0.2044 0.01369 0.00791 -0.0566 0.9784 0.4965
-2.750 -0.1763 0.01376 0.00796 -0.0567 0.9749 0.5524
-2.500 -0.1461 0.01396 0.00815 -0.0572 0.9719 0.5993
-2.250 -0.1133 0.01418 0.00833 -0.0583 0.9695 0.6290
-2.000 -0.0867 0.01428 0.00838 -0.0582 0.9659 0.6511
-1.750 -0.0602 0.01439 0.00843 -0.0579 0.9619 0.6773
-1.500 -0.0297 0.01451 0.00857 -0.0585 0.9588 0.6990
-1.250 0.0051 0.01463 0.00865 -0.0601 0.9565 0.7135
-1.000 0.0298 0.01465 0.00866 -0.0598 0.9520 0.7256
-0.750 0.0591 0.01469 0.00870 -0.0604 0.9480 0.7388
-0.500 0.0929 0.01475 0.00874 -0.0619 0.9451 0.7527
-0.250 0.1278 0.01483 0.00884 -0.0635 0.9426 0.7679
0.000 0.1490 0.01483 0.00889 -0.0625 0.9365 0.7838
0.250 0.1817 0.01484 0.00897 -0.0636 0.9330 0.8016
0.500 0.2182 0.01484 0.00906 -0.0654 0.9305 0.8231
0.750 0.2366 0.01482 0.00916 -0.0636 0.9234 0.8493
1.000 0.2694 0.01471 0.00919 -0.0645 0.9197 0.8854
1.250 0.3193 0.01453 0.00918 -0.0690 0.9178 0.9604
1.500 0.3494 0.01459 0.00923 -0.0702 0.9106 1.0000
1.750 0.3916 0.01453 0.00919 -0.0733 0.9065 1.0000
2.000 0.4296 0.01447 0.00923 -0.0755 0.9009 1.0000
2.250 0.4705 0.01422 0.00906 -0.0779 0.8944 1.0000
2.500 0.5337 0.01339 0.00837 -0.0841 0.8912 1.0000
2.750 0.5920 0.01216 0.00728 -0.0886 0.8791 1.0000
3.000 0.6405 0.01119 0.00653 -0.0913 0.8655 1.0000
3.250 0.6733 0.01069 0.00614 -0.0913 0.8481 1.0000
3.500 0.7052 0.01006 0.00561 -0.0906 0.8193 1.0000
3.750 0.7309 0.00961 0.00516 -0.0887 0.7655 1.0000
4.000 0.7532 0.00972 0.00474 -0.0861 0.6160 1.0000
4.250 0.7489 0.01154 0.00524 -0.0797 0.3779 1.0000
4.500 0.7460 0.01395 0.00628 -0.0747 0.1318 1.0000
4.750 0.7569 0.01579 0.00750 -0.0718 0.0454 1.0000
5.000 0.7728 0.01736 0.00897 -0.0694 0.0176 1.0000
5.250 0.7883 0.01942 0.01111 -0.0670 0.0131 1.0000
5.500 0.8117 0.02108 0.01290 -0.0658 0.0119 1.0000
5.750 0.8392 0.02347 0.01561 -0.0651 0.0111 1.0000
6.000 0.8675 0.02629 0.01874 -0.0645 0.0111 1.0000
6.250 0.8925 0.02958 0.02245 -0.0632 0.0114 1.0000
6.500 0.9119 0.03332 0.02666 -0.0612 0.0120 1.0000
6.750 0.9243 0.03793 0.03174 -0.0585 0.0129 1.0000
7.000 0.9546 0.04634 0.04093 -0.0540 0.0389 1.0000
7.250 0.9669 0.05069 0.04537 -0.0525 0.0379 1.0000
7.500 0.9604 0.05424 0.04956 -0.0479 0.0343 1.0000
7.750 0.9635 0.05759 0.05326 -0.0447 0.0324 1.0000
8.000 0.9634 0.06131 0.05725 -0.0419 0.0312 1.0000
8.250 0.9601 0.06508 0.06124 -0.0393 0.0304 1.0000
8.500 0.9535 0.06879 0.06515 -0.0368 0.0297 1.0000
8.750 0.9429 0.07230 0.06880 -0.0341 0.0292 1.0000
9.000 0.9274 0.07564 0.07226 -0.0313 0.0290 1.0000
9.250 0.9100 0.07935 0.07609 -0.0296 0.0288 1.0000
9.500 0.8912 0.08370 0.08054 -0.0294 0.0288 1.0000
9.750 0.8722 0.08892 0.08584 -0.0310 0.0289 1.0000
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Polar data table (+)
Polar graphs
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