E214 (11.1%) (e214-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 50,000 Max Cl/Cd: 39.85 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e214-il-50000-n5.txt Download as CSV file: xf-e214-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E214 (11.1%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3572 0.10580 0.09903 -0.0404 1.0000 0.0614
-8.500 -0.3599 0.10282 0.09613 -0.0397 1.0000 0.0595
-8.250 -0.3661 0.09992 0.09333 -0.0391 1.0000 0.0585
-8.000 -0.3743 0.09722 0.09074 -0.0384 1.0000 0.0581
-7.500 -0.4241 0.08888 0.08270 -0.0417 1.0000 0.0513
-7.250 -0.4296 0.08545 0.07934 -0.0420 1.0000 0.0511
-7.000 -0.4347 0.08165 0.07559 -0.0431 1.0000 0.0509
-6.750 -0.4406 0.07722 0.07118 -0.0452 1.0000 0.0508
-6.500 -0.4442 0.07273 0.06664 -0.0473 1.0000 0.0508
-6.250 -0.4440 0.06831 0.06212 -0.0495 1.0000 0.0507
-6.000 -0.4400 0.06341 0.05702 -0.0524 1.0000 0.0508
-5.750 -0.4264 0.05842 0.05172 -0.0562 0.9988 0.0508
-5.500 -0.3947 0.05264 0.04546 -0.0629 0.9933 0.0507
-5.250 -0.3606 0.04746 0.03968 -0.0687 0.9879 0.0507
-5.000 -0.3226 0.04301 0.03450 -0.0738 0.9836 0.0511
-4.750 -0.2884 0.03957 0.03053 -0.0772 0.9782 0.0522
-4.500 -0.2533 0.03759 0.02835 -0.0802 0.9730 0.0562
-4.250 -0.2179 0.03543 0.02570 -0.0826 0.9675 0.0596
-4.000 -0.1815 0.03340 0.02316 -0.0846 0.9621 0.0618
-3.750 -0.1458 0.03186 0.02116 -0.0861 0.9569 0.0644
-3.500 -0.1146 0.03057 0.01984 -0.0870 0.9503 0.0685
-3.250 -0.0785 0.02969 0.01867 -0.0887 0.9448 0.0780
-3.000 -0.0488 0.02878 0.01776 -0.0895 0.9371 0.0891
-2.750 -0.0094 0.02772 0.01670 -0.0921 0.9322 0.1124
-2.500 0.0231 0.02652 0.01590 -0.0941 0.9244 0.1879
-2.250 0.0601 0.02507 0.01582 -0.0969 0.9195 0.4374
-2.000 0.0838 0.02505 0.01604 -0.0955 0.9104 0.5812
-1.750 0.1132 0.02507 0.01606 -0.0947 0.9039 0.6648
-1.500 0.1324 0.02508 0.01606 -0.0924 0.8938 0.7174
-1.250 0.1541 0.02501 0.01595 -0.0904 0.8851 0.7654
-1.000 0.1776 0.02484 0.01573 -0.0887 0.8772 0.8131
-0.750 0.1948 0.02466 0.01552 -0.0861 0.8672 0.8613
-0.500 0.2350 0.02428 0.01504 -0.0879 0.8614 0.9430
-0.250 0.2689 0.02431 0.01484 -0.0901 0.8506 1.0000
0.000 0.3046 0.02447 0.01473 -0.0924 0.8421 1.0000
0.250 0.3434 0.02455 0.01457 -0.0949 0.8349 1.0000
0.500 0.3744 0.02478 0.01461 -0.0962 0.8253 1.0000
0.750 0.4151 0.02476 0.01440 -0.0987 0.8194 1.0000
1.000 0.4430 0.02503 0.01454 -0.0992 0.8089 1.0000
1.250 0.4783 0.02511 0.01449 -0.1007 0.8014 1.0000
1.500 0.5111 0.02524 0.01453 -0.1018 0.7928 1.0000
1.750 0.5405 0.02547 0.01468 -0.1023 0.7831 1.0000
2.000 0.5796 0.02542 0.01455 -0.1042 0.7767 1.0000
2.250 0.6059 0.02573 0.01483 -0.1042 0.7659 1.0000
2.500 0.6401 0.02581 0.01488 -0.1053 0.7578 1.0000
2.750 0.6733 0.02591 0.01496 -0.1062 0.7491 1.0000
3.000 0.7007 0.02619 0.01527 -0.1062 0.7385 1.0000
3.250 0.7407 0.02603 0.01510 -0.1079 0.7319 1.0000
3.500 0.7660 0.02637 0.01548 -0.1076 0.7204 1.0000
3.750 0.7931 0.02665 0.01583 -0.1075 0.7094 1.0000
4.000 0.8265 0.02669 0.01592 -0.1081 0.7002 1.0000
4.250 0.8586 0.02677 0.01606 -0.1086 0.6901 1.0000
4.500 0.8840 0.02711 0.01647 -0.1081 0.6779 1.0000
4.750 0.9113 0.02736 0.01685 -0.1079 0.6661 1.0000
5.000 0.9409 0.02751 0.01709 -0.1079 0.6545 1.0000
5.250 0.9727 0.02756 0.01723 -0.1081 0.6429 1.0000
5.500 1.0038 0.02761 0.01743 -0.1082 0.6304 1.0000
5.750 1.0295 0.02785 0.01779 -0.1075 0.6163 1.0000
6.000 1.0554 0.02807 0.01813 -0.1069 0.6016 1.0000
6.250 1.0803 0.02830 0.01848 -0.1060 0.5862 1.0000
6.500 1.1007 0.02868 0.01901 -0.1045 0.5692 1.0000
6.750 1.1216 0.02902 0.01953 -0.1031 0.5514 1.0000
7.000 1.1438 0.02925 0.01989 -0.1017 0.5329 1.0000
7.250 1.1677 0.02938 0.02011 -0.1005 0.5136 1.0000
7.500 1.1820 0.02992 0.02080 -0.0981 0.4922 1.0000
7.750 1.2022 0.03017 0.02111 -0.0963 0.4703 1.0000
8.000 1.2138 0.03080 0.02192 -0.0936 0.4464 1.0000
8.250 1.2259 0.03136 0.02255 -0.0909 0.4216 1.0000
8.500 1.2363 0.03202 0.02323 -0.0880 0.3955 1.0000
8.750 1.2444 0.03286 0.02408 -0.0850 0.3682 1.0000
9.000 1.2504 0.03390 0.02510 -0.0819 0.3402 1.0000
9.250 1.2544 0.03515 0.02634 -0.0788 0.3119 1.0000
9.500 1.2570 0.03663 0.02778 -0.0759 0.2840 1.0000
9.750 1.2581 0.03835 0.02949 -0.0731 0.2570 1.0000
10.000 1.2585 0.04028 0.03138 -0.0705 0.2319 1.0000
10.250 1.2580 0.04242 0.03345 -0.0682 0.2095 1.0000
10.500 1.2573 0.04475 0.03576 -0.0661 0.1885 1.0000
10.750 1.2562 0.04725 0.03821 -0.0642 0.1710 1.0000
11.000 1.2554 0.04988 0.04083 -0.0627 0.1544 1.0000
11.250 1.2551 0.05262 0.04360 -0.0613 0.1397 1.0000
11.500 1.2548 0.05546 0.04645 -0.0601 0.1270 1.0000
11.750 1.2541 0.05841 0.04941 -0.0592 0.1159 1.0000
12.000 1.2556 0.06137 0.05250 -0.0583 0.1050 1.0000
12.250 1.2564 0.06448 0.05574 -0.0576 0.0954 1.0000
12.500 1.2563 0.06769 0.05905 -0.0570 0.0873 1.0000
12.750 1.2566 0.07099 0.06248 -0.0566 0.0797 1.0000
13.000 1.2565 0.07451 0.06618 -0.0564 0.0728 1.0000
13.250 1.2551 0.07807 0.06983 -0.0564 0.0670 1.0000
13.500 1.2541 0.08197 0.07394 -0.0564 0.0617 1.0000
13.750 1.2498 0.08620 0.07838 -0.0571 0.0570 1.0000
14.000 1.2493 0.08983 0.08195 -0.0574 0.0531 1.0000
14.250 1.2418 0.09515 0.08771 -0.0587 0.0501 1.0000
14.500 1.2340 0.10045 0.09327 -0.0604 0.0475 1.0000
14.750 1.2275 0.10545 0.09842 -0.0622 0.0452 1.0000
15.000 1.2277 0.10921 0.10211 -0.0631 0.0427 1.0000
15.250 1.2142 0.11620 0.10945 -0.0664 0.0420 1.0000
15.500 1.1991 0.12380 0.11735 -0.0704 0.0415 1.0000
15.750 1.1825 0.13215 0.12596 -0.0752 0.0413 1.0000
16.000 1.1647 0.14140 0.13542 -0.0810 0.0414 1.0000
16.250 1.1460 0.15157 0.14576 -0.0874 0.0417 1.0000
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Polar data table (+)
Polar graphs
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