E211 (10.96%) (e211-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.68 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e211-il-1000000-n5.txt Download as CSV file: xf-e211-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5193 0.10606 0.10437 -0.0292 1.0000 0.0063
-11.500 -0.7561 0.04717 0.04495 -0.0627 0.9996 0.0058
-11.250 -0.7694 0.03957 0.03709 -0.0723 0.9970 0.0058
-11.000 -0.7706 0.03517 0.03247 -0.0782 0.9937 0.0058
-10.750 -0.7697 0.03020 0.02709 -0.0816 0.9894 0.0059
-10.500 -0.7540 0.02696 0.02355 -0.0840 0.9872 0.0059
-10.250 -0.7320 0.02429 0.02060 -0.0864 0.9857 0.0060
-10.000 -0.7043 0.02241 0.01852 -0.0887 0.9847 0.0061
-9.750 -0.6861 0.02108 0.01704 -0.0881 0.9810 0.0062
-9.500 -0.6600 0.01998 0.01582 -0.0890 0.9784 0.0063
-9.250 -0.6315 0.01892 0.01464 -0.0902 0.9767 0.0064
-9.000 -0.6015 0.01808 0.01371 -0.0915 0.9753 0.0066
-8.750 -0.5712 0.01719 0.01270 -0.0929 0.9743 0.0067
-8.500 -0.5403 0.01630 0.01172 -0.0943 0.9735 0.0068
-8.250 -0.5090 0.01545 0.01076 -0.0957 0.9728 0.0070
-8.000 -0.4937 0.01478 0.01001 -0.0935 0.9678 0.0071
-7.750 -0.4669 0.01405 0.00918 -0.0937 0.9653 0.0073
-7.500 -0.4375 0.01338 0.00843 -0.0945 0.9635 0.0075
-7.250 -0.4069 0.01273 0.00772 -0.0955 0.9621 0.0077
-7.000 -0.3753 0.01216 0.00708 -0.0966 0.9609 0.0079
-6.750 -0.3429 0.01164 0.00650 -0.0979 0.9599 0.0081
-6.500 -0.3271 0.01129 0.00610 -0.0955 0.9526 0.0083
-6.250 -0.2979 0.01085 0.00562 -0.0959 0.9496 0.0084
-6.000 -0.2669 0.01045 0.00518 -0.0968 0.9474 0.0085
-5.750 -0.2461 0.01006 0.00475 -0.0954 0.9396 0.0087
-5.500 -0.2153 0.00948 0.00410 -0.0963 0.9353 0.0091
-5.250 -0.1840 0.00907 0.00365 -0.0971 0.9297 0.0094
-5.000 -0.1480 0.00871 0.00326 -0.0990 0.9236 0.0100
-4.750 -0.1088 0.00840 0.00291 -0.1016 0.9165 0.0106
-4.500 -0.0690 0.00811 0.00255 -0.1043 0.9056 0.0113
-4.250 -0.0334 0.00790 0.00226 -0.1060 0.8881 0.0119
-4.000 -0.0023 0.00778 0.00203 -0.1067 0.8668 0.0126
-3.750 0.0256 0.00770 0.00183 -0.1067 0.8438 0.0144
-3.500 0.0519 0.00763 0.00168 -0.1064 0.8209 0.0180
-3.250 0.0774 0.00743 0.00151 -0.1060 0.7995 0.0481
-3.000 0.1029 0.00727 0.00138 -0.1056 0.7786 0.0793
-2.750 0.1284 0.00711 0.00128 -0.1052 0.7592 0.1200
-2.500 0.1543 0.00698 0.00120 -0.1049 0.7408 0.1573
-2.250 0.1803 0.00682 0.00112 -0.1047 0.7232 0.2057
-2.000 0.2065 0.00671 0.00106 -0.1045 0.7067 0.2465
-1.750 0.2326 0.00645 0.00099 -0.1044 0.6910 0.3258
-1.500 0.2587 0.00610 0.00095 -0.1044 0.6765 0.4425
-1.250 0.2854 0.00602 0.00095 -0.1042 0.6624 0.4942
-1.000 0.3125 0.00605 0.00096 -0.1040 0.6494 0.5153
-0.750 0.3396 0.00607 0.00098 -0.1039 0.6368 0.5351
-0.500 0.3668 0.00611 0.00100 -0.1037 0.6245 0.5494
0.000 0.4214 0.00621 0.00105 -0.1035 0.6010 0.5723
0.250 0.4487 0.00626 0.00108 -0.1033 0.5893 0.5828
0.500 0.4759 0.00633 0.00112 -0.1032 0.5773 0.5925
0.750 0.5028 0.00641 0.00117 -0.1030 0.5631 0.6023
1.000 0.5297 0.00649 0.00122 -0.1028 0.5482 0.6116
1.250 0.5567 0.00658 0.00128 -0.1026 0.5336 0.6211
1.500 0.5836 0.00666 0.00134 -0.1024 0.5198 0.6309
1.750 0.6104 0.00676 0.00141 -0.1022 0.5050 0.6401
2.000 0.6371 0.00687 0.00150 -0.1020 0.4880 0.6488
2.250 0.6636 0.00700 0.00158 -0.1017 0.4696 0.6562
2.500 0.6899 0.00715 0.00168 -0.1015 0.4507 0.6637
2.750 0.7162 0.00729 0.00179 -0.1012 0.4317 0.6708
3.000 0.7421 0.00747 0.00190 -0.1008 0.4093 0.6789
3.250 0.7680 0.00765 0.00204 -0.1005 0.3882 0.6870
3.750 0.8185 0.00813 0.00236 -0.0996 0.3344 0.7044
4.000 0.8403 0.00867 0.00264 -0.0986 0.2722 0.7140
4.500 0.8840 0.00976 0.00327 -0.0967 0.1659 0.7359
4.750 0.9079 0.01010 0.00354 -0.0961 0.1398 0.7473
5.000 0.9311 0.01049 0.00383 -0.0953 0.1113 0.7604
5.250 0.9543 0.01086 0.00413 -0.0946 0.0879 0.7755
5.500 0.9771 0.01126 0.00446 -0.0937 0.0651 0.7918
5.750 0.9991 0.01170 0.00483 -0.0927 0.0428 0.8099
6.000 1.0210 0.01212 0.00522 -0.0917 0.0272 0.8301
6.250 1.0410 0.01263 0.00569 -0.0903 0.0101 0.8564
6.500 1.0616 0.01286 0.00603 -0.0889 0.0078 0.8941
6.750 1.0823 0.01300 0.00632 -0.0874 0.0071 1.0000
7.000 1.1056 0.01337 0.00671 -0.0867 0.0065 1.0000
7.250 1.1285 0.01376 0.00714 -0.0858 0.0059 1.0000
7.500 1.1508 0.01419 0.00759 -0.0849 0.0055 1.0000
7.750 1.1734 0.01457 0.00801 -0.0841 0.0053 1.0000
8.000 1.1955 0.01496 0.00844 -0.0832 0.0051 1.0000
8.250 1.2170 0.01540 0.00892 -0.0822 0.0048 1.0000
8.500 1.2379 0.01587 0.00943 -0.0811 0.0047 1.0000
8.750 1.2580 0.01637 0.00997 -0.0798 0.0045 1.0000
9.000 1.2775 0.01689 0.01054 -0.0785 0.0043 1.0000
9.250 1.2959 0.01743 0.01113 -0.0770 0.0042 1.0000
9.500 1.3126 0.01799 0.01174 -0.0752 0.0041 1.0000
9.750 1.3276 0.01861 0.01242 -0.0731 0.0040 1.0000
10.000 1.3417 0.01929 0.01316 -0.0709 0.0038 1.0000
10.250 1.3537 0.02009 0.01403 -0.0684 0.0037 1.0000
10.500 1.3642 0.02099 0.01500 -0.0658 0.0036 1.0000
10.750 1.3701 0.02219 0.01632 -0.0626 0.0035 1.0000
11.000 1.3827 0.02294 0.01713 -0.0605 0.0035 1.0000
11.250 1.3922 0.02392 0.01819 -0.0580 0.0035 1.0000
11.500 1.4039 0.02476 0.01911 -0.0560 0.0034 1.0000
11.750 1.4116 0.02588 0.02033 -0.0536 0.0034 1.0000
12.000 1.4215 0.02688 0.02140 -0.0516 0.0033 1.0000
12.250 1.4272 0.02822 0.02284 -0.0492 0.0033 1.0000
12.500 1.4330 0.02960 0.02431 -0.0471 0.0032 1.0000
12.750 1.4377 0.03113 0.02594 -0.0451 0.0032 1.0000
13.000 1.4414 0.03281 0.02773 -0.0432 0.0032 1.0000
13.250 1.4438 0.03470 0.02972 -0.0415 0.0031 1.0000
13.500 1.4457 0.03674 0.03187 -0.0401 0.0031 1.0000
13.750 1.4463 0.03902 0.03426 -0.0389 0.0030 1.0000
14.000 1.4463 0.04150 0.03687 -0.0380 0.0030 1.0000
14.250 1.4444 0.04432 0.03981 -0.0373 0.0029 1.0000
14.500 1.4408 0.04749 0.04311 -0.0369 0.0029 1.0000
14.750 1.4373 0.05084 0.04658 -0.0370 0.0029 1.0000
15.000 1.4312 0.05469 0.05057 -0.0373 0.0029 1.0000
15.250 1.4267 0.05853 0.05453 -0.0380 0.0028 1.0000
15.500 1.4189 0.06303 0.05916 -0.0391 0.0028 1.0000
15.750 1.4113 0.06771 0.06398 -0.0406 0.0028 1.0000
16.000 1.4012 0.07300 0.06941 -0.0425 0.0028 1.0000
16.250 1.3909 0.07859 0.07513 -0.0448 0.0028 1.0000
16.500 1.3804 0.08447 0.08115 -0.0474 0.0028 1.0000
16.750 1.3678 0.09094 0.08776 -0.0505 0.0027 1.0000
17.000 1.3543 0.09786 0.09481 -0.0540 0.0027 1.0000
17.250 1.3394 0.10534 0.10244 -0.0580 0.0027 1.0000
17.500 1.3242 0.11309 0.11032 -0.0622 0.0027 1.0000
17.750 1.3084 0.12125 0.11862 -0.0669 0.0027 1.0000
18.000 1.2918 0.12980 0.12731 -0.0719 0.0027 1.0000
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Polar data table (+)
Polar graphs
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