E214 (11.1%) (e214-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 100,000 Max Cl/Cd: 61.9 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e214-il-100000.txt Download as CSV file: xf-e214-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2911 0.10601 0.10175 -0.0321 1.0000 0.0981
-8.750 -0.3119 0.10450 0.10033 -0.0329 1.0000 0.0998
-8.500 -0.3358 0.10314 0.09908 -0.0335 1.0000 0.1004
-8.250 -0.3087 0.09800 0.09393 -0.0293 1.0000 0.1041
-8.000 -0.3092 0.09587 0.09184 -0.0274 1.0000 0.1082
-7.750 -0.3219 0.09390 0.08995 -0.0266 1.0000 0.1119
-7.500 -0.3885 0.09643 0.09213 -0.0290 1.0000 0.1053
-7.250 -0.3964 0.09470 0.09047 -0.0268 1.0000 0.1085
-7.000 -0.4153 0.09338 0.08926 -0.0245 1.0000 0.1110
-6.750 -0.4346 0.09165 0.08764 -0.0238 1.0000 0.1124
-6.500 -0.4612 0.08788 0.08395 -0.0336 1.0000 0.1145
-6.250 -0.4592 0.08498 0.08113 -0.0278 1.0000 0.1169
-6.000 -0.4541 0.08373 0.07992 -0.0224 1.0000 0.1216
-5.750 -0.4647 0.07674 0.07270 -0.0414 1.0000 0.1297
-5.500 -0.4604 0.07544 0.07165 -0.0311 1.0000 0.1322
-5.250 -0.4562 0.07361 0.06985 -0.0285 1.0000 0.1366
-5.000 -0.4123 0.06527 0.06108 -0.0493 0.9923 0.1595
-4.750 -0.3898 0.06265 0.05862 -0.0468 0.9868 0.1639
-4.500 -0.3495 0.05737 0.05305 -0.0577 0.9794 0.1899
-4.250 -0.2840 0.04472 0.03933 -0.0741 0.9761 0.1326
-4.000 -0.2143 0.03398 0.02633 -0.0823 0.9753 0.0730
-3.750 -0.1688 0.03134 0.02319 -0.0860 0.9714 0.0721
-3.500 -0.1319 0.02947 0.02090 -0.0879 0.9642 0.0724
-3.250 -0.0898 0.02755 0.01888 -0.0910 0.9599 0.0772
-3.000 -0.0550 0.02660 0.01778 -0.0925 0.9521 0.0835
-2.750 -0.0131 0.02538 0.01657 -0.0950 0.9472 0.0911
-2.500 0.0213 0.02450 0.01578 -0.0965 0.9394 0.1081
-2.250 0.0655 0.02233 0.01472 -0.1005 0.9350 0.2935
-2.000 0.0955 0.02182 0.01536 -0.1007 0.9277 0.5975
-1.500 0.1492 0.02212 0.01577 -0.0985 0.9104 0.7349
-1.250 0.1825 0.02209 0.01571 -0.0984 0.9045 0.7820
-1.000 0.2003 0.02207 0.01569 -0.0959 0.8938 0.8181
-0.750 0.2232 0.02195 0.01553 -0.0942 0.8854 0.8575
-0.500 0.2470 0.02164 0.01522 -0.0924 0.8776 0.9022
-0.250 0.2851 0.02134 0.01490 -0.0945 0.8682 1.0000
0.000 0.3372 0.02123 0.01456 -0.0999 0.8629 1.0000
0.250 0.3750 0.02136 0.01452 -0.1028 0.8536 1.0000
0.500 0.4245 0.02115 0.01415 -0.1071 0.8486 1.0000
0.750 0.4584 0.02127 0.01415 -0.1088 0.8389 1.0000
1.000 0.5071 0.02090 0.01366 -0.1125 0.8344 1.0000
1.250 0.5393 0.02099 0.01366 -0.1136 0.8248 1.0000
1.500 0.5882 0.02054 0.01314 -0.1171 0.8202 1.0000
1.750 0.6209 0.02057 0.01312 -0.1180 0.8107 1.0000
2.000 0.6681 0.02011 0.01262 -0.1211 0.8055 1.0000
2.250 0.6989 0.02015 0.01264 -0.1216 0.7954 1.0000
2.500 0.7467 0.01960 0.01207 -0.1246 0.7902 1.0000
2.750 0.7754 0.01969 0.01217 -0.1247 0.7789 1.0000
3.000 0.8115 0.01954 0.01202 -0.1258 0.7699 1.0000
3.250 0.8521 0.01922 0.01169 -0.1276 0.7616 1.0000
3.500 0.8810 0.01930 0.01182 -0.1276 0.7497 1.0000
3.750 0.9127 0.01930 0.01184 -0.1279 0.7383 1.0000
4.000 0.9478 0.01919 0.01173 -0.1288 0.7274 1.0000
4.250 0.9848 0.01901 0.01158 -0.1299 0.7163 1.0000
4.500 1.0125 0.01914 0.01174 -0.1295 0.7027 1.0000
4.750 1.0405 0.01926 0.01189 -0.1292 0.6886 1.0000
5.000 1.0686 0.01937 0.01205 -0.1288 0.6742 1.0000
5.250 1.0966 0.01946 0.01218 -0.1284 0.6592 1.0000
5.500 1.1246 0.01954 0.01228 -0.1279 0.6436 1.0000
5.750 1.1494 0.01970 0.01248 -0.1269 0.6266 1.0000
6.000 1.1723 0.01989 0.01276 -0.1256 0.6087 1.0000
6.250 1.1962 0.02004 0.01296 -0.1245 0.5903 1.0000
6.500 1.2214 0.02014 0.01307 -0.1235 0.5714 1.0000
6.750 1.2421 0.02033 0.01332 -0.1218 0.5505 1.0000
7.000 1.2631 0.02049 0.01353 -0.1201 0.5283 1.0000
7.250 1.2813 0.02073 0.01382 -0.1179 0.5045 1.0000
7.500 1.2992 0.02099 0.01408 -0.1158 0.4792 1.0000
7.750 1.3144 0.02133 0.01442 -0.1132 0.4515 1.0000
8.000 1.3265 0.02178 0.01487 -0.1102 0.4207 1.0000
8.250 1.3361 0.02235 0.01544 -0.1068 0.3869 1.0000
8.500 1.3428 0.02310 0.01606 -0.1031 0.3512 1.0000
8.750 1.3460 0.02403 0.01688 -0.0989 0.3132 1.0000
9.000 1.3457 0.02521 0.01784 -0.0944 0.2772 1.0000
9.250 1.3448 0.02661 0.01907 -0.0901 0.2416 1.0000
9.500 1.3433 0.02826 0.02050 -0.0861 0.2105 1.0000
9.750 1.3424 0.03005 0.02212 -0.0823 0.1829 1.0000
10.000 1.3426 0.03197 0.02390 -0.0790 0.1594 1.0000
10.250 1.3433 0.03398 0.02577 -0.0760 0.1399 1.0000
10.500 1.3457 0.03610 0.02778 -0.0733 0.1226 1.0000
10.750 1.3487 0.03821 0.02993 -0.0708 0.1073 1.0000
11.000 1.3513 0.04042 0.03213 -0.0685 0.0940 1.0000
11.250 1.3537 0.04274 0.03444 -0.0664 0.0823 1.0000
11.500 1.3580 0.04521 0.03684 -0.0647 0.0718 1.0000
11.750 1.3603 0.04758 0.03935 -0.0628 0.0635 1.0000
12.000 1.3675 0.05036 0.04226 -0.0612 0.0558 1.0000
12.250 1.3879 0.05349 0.04528 -0.0605 0.0491 1.0000
12.500 1.3915 0.05626 0.04843 -0.0588 0.0458 1.0000
12.750 1.3942 0.05900 0.05136 -0.0574 0.0427 1.0000
13.000 1.4151 0.06320 0.05556 -0.0573 0.0392 1.0000
13.250 1.4098 0.06675 0.05950 -0.0556 0.0386 1.0000
13.500 1.4023 0.07078 0.06390 -0.0543 0.0381 1.0000
13.750 1.3914 0.07521 0.06869 -0.0533 0.0377 1.0000
14.000 1.3775 0.08003 0.07384 -0.0529 0.0375 1.0000
14.250 1.3611 0.08525 0.07939 -0.0531 0.0374 1.0000
14.500 1.3426 0.09089 0.08532 -0.0539 0.0374 1.0000
14.750 1.3226 0.09696 0.09167 -0.0556 0.0375 1.0000
15.000 1.3015 0.10352 0.09849 -0.0580 0.0377 1.0000
15.250 1.2798 0.11060 0.10579 -0.0612 0.0379 1.0000
15.500 1.2580 0.11820 0.11360 -0.0653 0.0382 1.0000
15.750 1.2361 0.12642 0.12200 -0.0701 0.0385 1.0000
16.000 1.2151 0.13516 0.13089 -0.0756 0.0389 1.0000
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Polar data table (+)
Polar graphs
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