E214 (11.1%) (e214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.24 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e214-il-1000000-n5.txt Download as CSV file: xf-e214-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4021 0.14812 0.14639 -0.0285 0.9999 0.0037
-13.250 -0.3926 0.14485 0.14311 -0.0306 0.9995 0.0038
-12.250 -0.7410 0.03214 0.02970 -0.1130 0.9850 0.0053
-12.000 -0.7277 0.02860 0.02590 -0.1178 0.9814 0.0054
-11.750 -0.7147 0.02571 0.02276 -0.1202 0.9765 0.0056
-11.500 -0.6873 0.02454 0.02150 -0.1222 0.9745 0.0058
-11.250 -0.6579 0.02351 0.02039 -0.1243 0.9731 0.0060
-11.000 -0.6274 0.02260 0.01940 -0.1263 0.9720 0.0062
-10.750 -0.6094 0.02184 0.01855 -0.1255 0.9668 0.0063
-10.500 -0.5840 0.02086 0.01747 -0.1264 0.9638 0.0065
-10.250 -0.5558 0.02006 0.01658 -0.1276 0.9619 0.0068
-10.000 -0.5275 0.01902 0.01538 -0.1289 0.9604 0.0071
-9.750 -0.4981 0.01801 0.01423 -0.1304 0.9592 0.0074
-9.500 -0.4785 0.01718 0.01328 -0.1295 0.9537 0.0076
-9.250 -0.4510 0.01640 0.01238 -0.1302 0.9506 0.0078
-9.000 -0.4205 0.01563 0.01148 -0.1315 0.9487 0.0080
-8.750 -0.3880 0.01478 0.01050 -0.1333 0.9471 0.0082
-8.500 -0.3558 0.01410 0.00975 -0.1349 0.9449 0.0087
-8.250 -0.3283 0.01373 0.00934 -0.1352 0.9401 0.0090
-8.000 -0.2960 0.01339 0.00896 -0.1365 0.9368 0.0093
-7.750 -0.2622 0.01287 0.00835 -0.1381 0.9338 0.0097
-7.500 -0.2312 0.01235 0.00775 -0.1392 0.9294 0.0101
-7.250 -0.2011 0.01185 0.00716 -0.1400 0.9238 0.0105
-7.000 -0.1687 0.01140 0.00661 -0.1413 0.9189 0.0109
-6.750 -0.1399 0.01108 0.00623 -0.1417 0.9124 0.0113
-6.500 -0.1095 0.01082 0.00590 -0.1424 0.9057 0.0115
-6.250 -0.0811 0.01051 0.00551 -0.1427 0.8984 0.0117
-6.000 -0.0531 0.00983 0.00470 -0.1431 0.8904 0.0121
-5.750 -0.0260 0.00934 0.00414 -0.1431 0.8815 0.0126
-5.500 0.0019 0.00903 0.00376 -0.1433 0.8724 0.0130
-5.250 0.0295 0.00879 0.00344 -0.1433 0.8620 0.0135
-5.000 0.0568 0.00859 0.00318 -0.1433 0.8509 0.0141
-4.750 0.0840 0.00840 0.00292 -0.1432 0.8386 0.0147
-4.500 0.1109 0.00824 0.00266 -0.1430 0.8251 0.0152
-4.250 0.1376 0.00810 0.00244 -0.1428 0.8106 0.0157
-4.000 0.1642 0.00800 0.00224 -0.1426 0.7957 0.0160
-3.750 0.1906 0.00791 0.00207 -0.1423 0.7805 0.0163
-3.500 0.2170 0.00782 0.00188 -0.1420 0.7658 0.0168
-3.250 0.2435 0.00774 0.00171 -0.1417 0.7514 0.0179
-3.000 0.2702 0.00768 0.00158 -0.1414 0.7378 0.0195
-2.750 0.2969 0.00763 0.00148 -0.1412 0.7251 0.0221
-2.500 0.3237 0.00749 0.00138 -0.1411 0.7130 0.0440
-2.250 0.3506 0.00739 0.00130 -0.1410 0.7013 0.0695
-2.000 0.3776 0.00726 0.00124 -0.1409 0.6898 0.1072
-1.750 0.4048 0.00715 0.00119 -0.1409 0.6787 0.1428
-1.500 0.4320 0.00703 0.00116 -0.1409 0.6681 0.1897
-1.250 0.4592 0.00691 0.00113 -0.1409 0.6575 0.2430
-1.000 0.4866 0.00667 0.00112 -0.1411 0.6469 0.3348
-0.750 0.5140 0.00640 0.00114 -0.1413 0.6366 0.4545
-0.500 0.5412 0.00638 0.00119 -0.1412 0.6265 0.5034
0.000 0.5956 0.00646 0.00125 -0.1410 0.6061 0.5404
0.250 0.6227 0.00651 0.00130 -0.1408 0.5962 0.5547
0.500 0.6496 0.00658 0.00134 -0.1406 0.5858 0.5685
0.750 0.6767 0.00664 0.00139 -0.1405 0.5752 0.5818
1.000 0.7037 0.00671 0.00145 -0.1403 0.5645 0.5937
1.250 0.7304 0.00679 0.00151 -0.1401 0.5526 0.6060
1.500 0.7569 0.00689 0.00159 -0.1398 0.5404 0.6184
1.750 0.7833 0.00699 0.00167 -0.1396 0.5277 0.6315
2.000 0.8098 0.00708 0.00176 -0.1393 0.5149 0.6453
2.250 0.8362 0.00718 0.00185 -0.1391 0.5021 0.6578
2.500 0.8624 0.00731 0.00195 -0.1388 0.4883 0.6688
2.750 0.8884 0.00744 0.00206 -0.1385 0.4735 0.6802
3.000 0.9139 0.00760 0.00219 -0.1380 0.4567 0.6920
3.250 0.9393 0.00777 0.00232 -0.1376 0.4387 0.7043
3.500 0.9647 0.00794 0.00246 -0.1372 0.4215 0.7181
3.750 0.9901 0.00810 0.00262 -0.1368 0.4056 0.7335
4.000 1.0149 0.00831 0.00279 -0.1363 0.3866 0.7498
4.250 1.0391 0.00854 0.00298 -0.1356 0.3652 0.7682
4.500 1.0624 0.00882 0.00320 -0.1348 0.3391 0.7904
4.750 1.0858 0.00905 0.00344 -0.1341 0.3166 0.8174
5.000 1.1080 0.00931 0.00368 -0.1330 0.2943 0.8507
5.250 1.1267 0.00954 0.00393 -0.1312 0.2699 0.9033
5.500 1.1464 0.00978 0.00414 -0.1296 0.2451 1.0000
5.750 1.1680 0.01025 0.00447 -0.1286 0.2157 1.0000
6.000 1.1885 0.01078 0.00483 -0.1274 0.1844 1.0000
6.250 1.2102 0.01121 0.00516 -0.1264 0.1617 1.0000
6.500 1.2311 0.01168 0.00552 -0.1253 0.1402 1.0000
6.750 1.2505 0.01224 0.00593 -0.1240 0.1143 1.0000
7.000 1.2692 0.01282 0.00638 -0.1225 0.0902 1.0000
7.250 1.2893 0.01329 0.00678 -0.1212 0.0753 1.0000
7.500 1.3086 0.01375 0.00718 -0.1198 0.0629 1.0000
7.750 1.3268 0.01421 0.00759 -0.1182 0.0525 1.0000
8.000 1.3441 0.01470 0.00803 -0.1164 0.0428 1.0000
8.250 1.3603 0.01523 0.00851 -0.1145 0.0330 1.0000
8.500 1.3767 0.01576 0.00901 -0.1126 0.0259 1.0000
8.750 1.3935 0.01626 0.00950 -0.1108 0.0210 1.0000
9.000 1.4097 0.01678 0.01002 -0.1089 0.0170 1.0000
9.250 1.4246 0.01740 0.01062 -0.1069 0.0122 1.0000
9.500 1.4386 0.01806 0.01127 -0.1048 0.0082 1.0000
9.750 1.4523 0.01874 0.01196 -0.1026 0.0057 1.0000
10.000 1.4661 0.01942 0.01268 -0.1006 0.0045 1.0000
10.250 1.4806 0.02006 0.01337 -0.0987 0.0041 1.0000
10.500 1.4943 0.02075 0.01411 -0.0967 0.0037 1.0000
10.750 1.5069 0.02153 0.01494 -0.0946 0.0034 1.0000
11.000 1.5189 0.02236 0.01582 -0.0926 0.0032 1.0000
11.250 1.5293 0.02331 0.01684 -0.0903 0.0029 1.0000
11.500 1.5402 0.02425 0.01784 -0.0883 0.0028 1.0000
11.750 1.5516 0.02517 0.01883 -0.0865 0.0027 1.0000
12.000 1.5619 0.02621 0.01995 -0.0845 0.0026 1.0000
12.250 1.5717 0.02730 0.02110 -0.0827 0.0024 1.0000
12.500 1.5802 0.02853 0.02241 -0.0808 0.0023 1.0000
12.750 1.5883 0.02984 0.02379 -0.0790 0.0023 1.0000
13.000 1.5953 0.03126 0.02530 -0.0772 0.0022 1.0000
13.250 1.6018 0.03280 0.02692 -0.0755 0.0021 1.0000
13.500 1.6074 0.03447 0.02867 -0.0740 0.0021 1.0000
13.750 1.6123 0.03626 0.03055 -0.0725 0.0020 1.0000
14.000 1.6162 0.03822 0.03260 -0.0711 0.0020 1.0000
14.250 1.6188 0.04039 0.03487 -0.0699 0.0019 1.0000
14.500 1.6208 0.04271 0.03729 -0.0688 0.0018 1.0000
14.750 1.6214 0.04530 0.03998 -0.0679 0.0018 1.0000
15.000 1.6209 0.04812 0.04291 -0.0672 0.0018 1.0000
15.250 1.6189 0.05124 0.04614 -0.0667 0.0017 1.0000
15.500 1.6157 0.05463 0.04965 -0.0665 0.0017 1.0000
15.750 1.6103 0.05848 0.05362 -0.0665 0.0016 1.0000
16.000 1.6056 0.06239 0.05765 -0.0668 0.0016 1.0000
16.250 1.5956 0.06720 0.06261 -0.0675 0.0016 1.0000
16.500 1.5860 0.07219 0.06774 -0.0685 0.0016 1.0000
16.750 1.5786 0.07703 0.07271 -0.0697 0.0015 1.0000
17.000 1.5720 0.08189 0.07769 -0.0712 0.0015 1.0000
17.250 1.5639 0.08713 0.08305 -0.0729 0.0015 1.0000
17.500 1.5552 0.09265 0.08870 -0.0749 0.0015 1.0000
17.750 1.5453 0.09855 0.09472 -0.0773 0.0015 1.0000
18.000 1.5338 0.10488 0.10119 -0.0800 0.0015 1.0000
18.250 1.5221 0.11139 0.10783 -0.0830 0.0015 1.0000
18.500 1.5100 0.11812 0.11469 -0.0863 0.0015 1.0000
18.750 1.4971 0.12517 0.12188 -0.0899 0.0015 1.0000
19.000 1.4834 0.13246 0.12931 -0.0939 0.0015 1.0000
19.250 1.4701 0.13981 0.13678 -0.0980 0.0015 1.0000
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Polar data table (+)
Polar graphs
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