E214 (11.1%) (e214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.91 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e214-il-1000000.txt Download as CSV file: xf-e214-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2877 0.08234 0.08073 -0.0669 0.9878 0.0125
-8.750 -0.2969 0.02770 0.02608 -0.1028 0.9748 0.0106
-8.500 -0.3233 0.01538 0.01308 -0.1214 0.9637 0.0103
-8.250 -0.3069 0.01024 0.00736 -0.1267 0.9612 0.0106
-8.000 -0.2782 0.00827 0.00504 -0.1296 0.9602 0.0110
-7.750 -0.2522 0.00555 0.00180 -0.1327 0.9590 0.0117
-7.500 -0.2472 0.01653 0.01248 -0.1355 0.9592 0.0120
-7.250 -0.2279 0.01600 0.01191 -0.1342 0.9531 0.0125
-7.000 -0.1958 0.01551 0.01138 -0.1355 0.9511 0.0132
-6.750 -0.1623 0.01443 0.01015 -0.1372 0.9494 0.0137
-6.500 -0.1289 0.01346 0.00903 -0.1387 0.9476 0.0142
-6.250 -0.0939 0.01263 0.00808 -0.1405 0.9460 0.0147
-6.000 -0.0686 0.01223 0.00760 -0.1400 0.9401 0.0151
-5.750 -0.0385 0.01081 0.00603 -0.1410 0.9359 0.0159
-5.500 -0.0039 0.01005 0.00524 -0.1428 0.9329 0.0170
-5.250 0.0234 0.00961 0.00476 -0.1428 0.9263 0.0177
-5.000 0.0552 0.00913 0.00421 -0.1438 0.9208 0.0182
-4.750 0.0852 0.00874 0.00375 -0.1444 0.9145 0.0189
-4.500 0.1149 0.00840 0.00335 -0.1448 0.9071 0.0196
-4.250 0.1440 0.00815 0.00304 -0.1451 0.8994 0.0203
-4.000 0.1734 0.00776 0.00255 -0.1455 0.8911 0.0217
-3.750 0.2013 0.00750 0.00222 -0.1455 0.8817 0.0234
-3.500 0.2299 0.00733 0.00199 -0.1456 0.8723 0.0252
-3.250 0.2581 0.00719 0.00179 -0.1456 0.8616 0.0273
-3.000 0.2854 0.00690 0.00158 -0.1456 0.8497 0.0594
-2.750 0.3127 0.00658 0.00143 -0.1457 0.8371 0.1221
-2.500 0.3399 0.00634 0.00133 -0.1457 0.8236 0.1821
-2.250 0.3668 0.00613 0.00124 -0.1456 0.8094 0.2484
-2.000 0.3936 0.00588 0.00118 -0.1456 0.7949 0.3329
-1.750 0.4202 0.00564 0.00115 -0.1456 0.7803 0.4335
-1.500 0.4468 0.00557 0.00117 -0.1454 0.7658 0.4949
-1.250 0.4734 0.00559 0.00118 -0.1451 0.7518 0.5291
-1.000 0.5001 0.00562 0.00121 -0.1448 0.7385 0.5543
-0.750 0.5268 0.00568 0.00123 -0.1445 0.7257 0.5766
-0.500 0.5534 0.00574 0.00126 -0.1442 0.7134 0.5924
-0.250 0.5800 0.00581 0.00129 -0.1439 0.7013 0.6047
0.000 0.6070 0.00586 0.00132 -0.1437 0.6896 0.6166
0.250 0.6339 0.00592 0.00136 -0.1434 0.6782 0.6286
0.500 0.6606 0.00598 0.00140 -0.1432 0.6673 0.6410
0.750 0.6872 0.00606 0.00145 -0.1429 0.6562 0.6536
1.000 0.7139 0.00613 0.00151 -0.1427 0.6449 0.6664
1.250 0.7407 0.00619 0.00157 -0.1424 0.6337 0.6800
1.500 0.7673 0.00626 0.00163 -0.1422 0.6223 0.6943
1.750 0.7936 0.00634 0.00171 -0.1418 0.6109 0.7101
2.250 0.8462 0.00648 0.00188 -0.1412 0.5873 0.7452
2.500 0.8724 0.00655 0.00197 -0.1409 0.5753 0.7640
2.750 0.8982 0.00664 0.00207 -0.1405 0.5626 0.7849
3.000 0.9236 0.00672 0.00218 -0.1399 0.5491 0.8091
3.250 0.9483 0.00680 0.00230 -0.1393 0.5350 0.8381
3.500 0.9715 0.00686 0.00242 -0.1383 0.5216 0.8767
3.750 0.9902 0.00681 0.00249 -0.1361 0.5088 0.9671
4.000 1.0170 0.00697 0.00260 -0.1360 0.4934 1.0000
4.250 1.0426 0.00716 0.00273 -0.1356 0.4765 1.0000
4.500 1.0679 0.00737 0.00288 -0.1352 0.4586 1.0000
4.750 1.0927 0.00761 0.00305 -0.1347 0.4400 1.0000
5.000 1.1174 0.00786 0.00322 -0.1342 0.4212 1.0000
5.250 1.1417 0.00812 0.00341 -0.1336 0.3997 1.0000
5.500 1.1654 0.00843 0.00363 -0.1329 0.3780 1.0000
5.750 1.1880 0.00881 0.00389 -0.1320 0.3490 1.0000
6.000 1.2101 0.00922 0.00416 -0.1311 0.3191 1.0000
6.250 1.2316 0.00966 0.00447 -0.1301 0.2886 1.0000
6.500 1.2528 0.01013 0.00480 -0.1290 0.2594 1.0000
6.750 1.2724 0.01069 0.00519 -0.1276 0.2252 1.0000
7.000 1.2904 0.01135 0.00565 -0.1260 0.1876 1.0000
7.250 1.3082 0.01200 0.00611 -0.1244 0.1543 1.0000
7.500 1.3258 0.01264 0.00659 -0.1227 0.1264 1.0000
7.750 1.3440 0.01319 0.00703 -0.1212 0.1058 1.0000
8.000 1.3605 0.01376 0.00751 -0.1193 0.0877 1.0000
8.250 1.3767 0.01431 0.00798 -0.1173 0.0727 1.0000
8.500 1.3927 0.01485 0.00846 -0.1153 0.0603 1.0000
8.750 1.4083 0.01542 0.00898 -0.1133 0.0491 1.0000
9.000 1.4234 0.01601 0.00952 -0.1112 0.0401 1.0000
9.250 1.4390 0.01657 0.01006 -0.1092 0.0333 1.0000
9.500 1.4541 0.01717 0.01065 -0.1072 0.0271 1.0000
9.750 1.4675 0.01785 0.01132 -0.1050 0.0210 1.0000
10.000 1.4782 0.01871 0.01214 -0.1024 0.0138 1.0000
10.250 1.4873 0.01969 0.01309 -0.0996 0.0091 1.0000
10.500 1.4996 0.02048 0.01394 -0.0974 0.0078 1.0000
10.750 1.5109 0.02134 0.01484 -0.0951 0.0069 1.0000
11.000 1.5185 0.02248 0.01605 -0.0923 0.0061 1.0000
11.250 1.5298 0.02337 0.01703 -0.0902 0.0059 1.0000
11.500 1.5403 0.02434 0.01807 -0.0881 0.0056 1.0000
11.750 1.5496 0.02542 0.01923 -0.0860 0.0053 1.0000
12.000 1.5578 0.02662 0.02051 -0.0838 0.0051 1.0000
12.250 1.5652 0.02792 0.02188 -0.0817 0.0049 1.0000
12.500 1.5699 0.02947 0.02351 -0.0795 0.0046 1.0000
12.750 1.5711 0.03137 0.02552 -0.0771 0.0044 1.0000
13.000 1.5646 0.03406 0.02836 -0.0744 0.0042 1.0000
13.250 1.5703 0.03577 0.03015 -0.0729 0.0041 1.0000
13.500 1.5738 0.03775 0.03222 -0.0715 0.0040 1.0000
13.750 1.5758 0.03998 0.03456 -0.0701 0.0040 1.0000
14.000 1.5766 0.04241 0.03711 -0.0689 0.0039 1.0000
14.250 1.5772 0.04499 0.03979 -0.0680 0.0038 1.0000
14.500 1.5755 0.04796 0.04287 -0.0672 0.0038 1.0000
14.750 1.5738 0.05106 0.04609 -0.0667 0.0037 1.0000
15.000 1.5711 0.05441 0.04956 -0.0664 0.0037 1.0000
15.250 1.5670 0.05809 0.05336 -0.0664 0.0036 1.0000
15.500 1.5628 0.06195 0.05734 -0.0666 0.0036 1.0000
15.750 1.5575 0.06608 0.06159 -0.0671 0.0036 1.0000
16.000 1.5512 0.07054 0.06618 -0.0679 0.0035 1.0000
16.250 1.5446 0.07521 0.07097 -0.0690 0.0035 1.0000
16.500 1.5369 0.08021 0.07610 -0.0703 0.0034 1.0000
16.750 1.5286 0.08546 0.08148 -0.0720 0.0034 1.0000
17.000 1.5200 0.09093 0.08707 -0.0739 0.0034 1.0000
17.250 1.5105 0.09672 0.09299 -0.0761 0.0034 1.0000
17.500 1.5009 0.10266 0.09907 -0.0786 0.0033 1.0000
17.750 1.4902 0.10892 0.10545 -0.0813 0.0033 1.0000
18.000 1.4802 0.11520 0.11186 -0.0843 0.0033 1.0000
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Polar data table (+)
Polar graphs
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