EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 50,000 Max Cl/Cd: 31.85 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e854-il-50000-n5.txt Download as CSV file: xf-e854-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E854 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3974 0.10427 0.09729 -0.0521 1.0000 0.0384
-10.250 -0.4016 0.09968 0.09279 -0.0534 1.0000 0.0384
-10.000 -0.4071 0.09495 0.08814 -0.0548 1.0000 0.0382
-9.750 -0.4144 0.09007 0.08334 -0.0563 1.0000 0.0380
-9.500 -0.4264 0.08484 0.07819 -0.0583 1.0000 0.0379
-9.250 -0.4403 0.08008 0.07351 -0.0598 1.0000 0.0375
-9.000 -0.4554 0.07600 0.06951 -0.0606 1.0000 0.0370
-8.750 -0.4790 0.07211 0.06570 -0.0610 1.0000 0.0367
-8.500 -0.5020 0.06897 0.06262 -0.0604 1.0000 0.0362
-8.250 -0.5219 0.06558 0.05922 -0.0599 1.0000 0.0358
-8.000 -0.5389 0.06224 0.05580 -0.0590 1.0000 0.0357
-7.750 -0.5516 0.05897 0.05238 -0.0580 1.0000 0.0356
-7.500 -0.5608 0.05553 0.04869 -0.0571 1.0000 0.0362
-7.250 -0.5640 0.05221 0.04503 -0.0563 1.0000 0.0367
-7.000 -0.5624 0.04883 0.04119 -0.0557 1.0000 0.0377
-6.750 -0.5379 0.04462 0.03636 -0.0587 0.9944 0.0391
-6.500 -0.5078 0.04133 0.03277 -0.0615 0.9871 0.0410
-6.250 -0.4755 0.03873 0.02976 -0.0639 0.9799 0.0449
-6.000 -0.4415 0.03628 0.02674 -0.0658 0.9727 0.0505
-5.750 -0.4115 0.03434 0.02475 -0.0670 0.9648 0.0562
-5.500 -0.3783 0.03265 0.02286 -0.0684 0.9577 0.0663
-5.250 -0.3485 0.03114 0.02123 -0.0693 0.9489 0.0791
-5.000 -0.3187 0.02967 0.01972 -0.0705 0.9402 0.0971
-4.750 -0.2847 0.02806 0.01810 -0.0728 0.9329 0.1277
-4.500 -0.2560 0.02628 0.01665 -0.0746 0.9234 0.1822
-4.250 -0.2253 0.02464 0.01611 -0.0768 0.9159 0.3417
-4.000 -0.1950 0.02485 0.01641 -0.0768 0.9066 0.4568
-3.750 -0.1668 0.02519 0.01657 -0.0764 0.8968 0.5097
-3.500 -0.1322 0.02547 0.01661 -0.0769 0.8902 0.5509
-3.250 -0.1082 0.02573 0.01674 -0.0755 0.8798 0.5804
-3.000 -0.0806 0.02591 0.01677 -0.0747 0.8714 0.6075
-2.750 -0.0507 0.02593 0.01665 -0.0744 0.8640 0.6286
-2.500 -0.0233 0.02588 0.01639 -0.0742 0.8552 0.6447
-2.250 0.0121 0.02568 0.01597 -0.0754 0.8489 0.6587
-2.000 0.0400 0.02558 0.01569 -0.0757 0.8399 0.6705
-1.750 0.0773 0.02536 0.01524 -0.0776 0.8342 0.6826
-1.500 0.1030 0.02533 0.01508 -0.0774 0.8249 0.6926
-1.250 0.1393 0.02512 0.01471 -0.0789 0.8194 0.7032
-1.000 0.1642 0.02515 0.01461 -0.0788 0.8100 0.7138
-0.750 0.2011 0.02495 0.01427 -0.0805 0.8047 0.7253
-0.500 0.2233 0.02505 0.01431 -0.0798 0.7952 0.7353
-0.250 0.2588 0.02488 0.01404 -0.0811 0.7902 0.7465
0.000 0.2803 0.02504 0.01417 -0.0804 0.7808 0.7581
0.250 0.3153 0.02489 0.01395 -0.0817 0.7758 0.7708
0.500 0.3352 0.02512 0.01417 -0.0807 0.7665 0.7840
0.750 0.3684 0.02500 0.01403 -0.0815 0.7615 0.7984
1.000 0.3865 0.02527 0.01433 -0.0801 0.7524 0.8137
1.250 0.4179 0.02516 0.01424 -0.0806 0.7474 0.8311
1.500 0.4351 0.02546 0.01461 -0.0791 0.7387 0.8520
1.750 0.4671 0.02537 0.01457 -0.0798 0.7336 0.8770
2.000 0.4931 0.02566 0.01495 -0.0801 0.7256 0.9134
2.250 0.5394 0.02565 0.01501 -0.0841 0.7201 1.0000
2.500 0.5657 0.02617 0.01547 -0.0851 0.7126 1.0000
2.750 0.5969 0.02653 0.01578 -0.0865 0.7064 1.0000
3.000 0.6250 0.02701 0.01623 -0.0874 0.7000 1.0000
3.250 0.6502 0.02756 0.01681 -0.0877 0.6928 1.0000
3.500 0.6858 0.02776 0.01701 -0.0893 0.6883 1.0000
3.750 0.7002 0.02871 0.01800 -0.0881 0.6791 1.0000
4.000 0.7361 0.02888 0.01823 -0.0895 0.6748 1.0000
4.250 0.7479 0.02996 0.01938 -0.0879 0.6654 1.0000
4.500 0.7828 0.03014 0.01962 -0.0891 0.6607 1.0000
4.750 0.7938 0.03128 0.02085 -0.0874 0.6512 1.0000
5.000 0.8292 0.03140 0.02110 -0.0885 0.6463 1.0000
5.250 0.8390 0.03258 0.02239 -0.0865 0.6363 1.0000
5.500 0.8771 0.03253 0.02247 -0.0878 0.6314 1.0000
5.750 0.8855 0.03373 0.02379 -0.0856 0.6206 1.0000
6.000 0.9066 0.03435 0.02459 -0.0848 0.6119 1.0000
6.250 0.9376 0.03444 0.02485 -0.0849 0.6040 1.0000
6.500 0.9504 0.03533 0.02590 -0.0830 0.5928 1.0000
6.750 0.9737 0.03563 0.02637 -0.0821 0.5824 1.0000
7.000 1.0133 0.03491 0.02589 -0.0826 0.5723 1.0000
7.250 1.0421 0.03453 0.02572 -0.0817 0.5590 1.0000
7.500 1.0606 0.03456 0.02593 -0.0797 0.5435 1.0000
7.750 1.0728 0.03482 0.02637 -0.0769 0.5266 1.0000
8.000 1.0847 0.03494 0.02667 -0.0740 0.5089 1.0000
8.250 1.1026 0.03462 0.02652 -0.0715 0.4894 1.0000
8.500 1.1092 0.03500 0.02711 -0.0682 0.4689 1.0000
8.750 1.1179 0.03521 0.02747 -0.0650 0.4450 1.0000
9.000 1.1189 0.03610 0.02850 -0.0616 0.4181 1.0000
9.250 1.1227 0.03688 0.02936 -0.0585 0.3851 1.0000
9.500 1.1266 0.03775 0.03017 -0.0556 0.3427 1.0000
9.750 1.1286 0.03899 0.03112 -0.0527 0.2930 1.0000
10.000 1.1237 0.04118 0.03295 -0.0500 0.2502 1.0000
10.250 1.1165 0.04393 0.03542 -0.0479 0.2176 1.0000
10.500 1.1095 0.04693 0.03823 -0.0463 0.1904 1.0000
10.750 1.1041 0.05001 0.04118 -0.0450 0.1672 1.0000
11.000 1.0996 0.05312 0.04415 -0.0439 0.1493 1.0000
11.250 1.0974 0.05615 0.04711 -0.0430 0.1326 1.0000
11.500 1.0969 0.05910 0.05009 -0.0423 0.1185 1.0000
11.750 1.0976 0.06200 0.05295 -0.0416 0.1063 1.0000
12.000 1.0989 0.06489 0.05582 -0.0410 0.0955 1.0000
12.250 1.1042 0.06754 0.05859 -0.0403 0.0853 1.0000
12.500 1.1093 0.07026 0.06142 -0.0396 0.0764 1.0000
12.750 1.1140 0.07296 0.06405 -0.0392 0.0694 1.0000
13.000 1.1223 0.07566 0.06706 -0.0385 0.0623 1.0000
13.250 1.1284 0.07840 0.06977 -0.0382 0.0568 1.0000
13.500 1.1354 0.08159 0.07335 -0.0377 0.0518 1.0000
13.750 1.1399 0.08467 0.07652 -0.0377 0.0480 1.0000
14.000 1.1414 0.08847 0.08050 -0.0379 0.0448 1.0000
14.250 1.1365 0.09327 0.08568 -0.0388 0.0426 1.0000
14.500 1.1305 0.09830 0.09102 -0.0401 0.0409 1.0000
14.750 1.1223 0.10370 0.09667 -0.0418 0.0398 1.0000
15.000 1.1122 0.10944 0.10263 -0.0441 0.0388 1.0000
15.250 1.1003 0.11571 0.10911 -0.0471 0.0382 1.0000
15.500 1.0858 0.12279 0.11638 -0.0508 0.0378 1.0000
15.750 1.0594 0.13333 0.12722 -0.0571 0.0388 1.0000
16.000 1.0270 0.14688 0.14098 -0.0658 0.0406 1.0000
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Polar data table (+)
Polar graphs
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