E210 (13.64%) (e210-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 100,000 Max Cl/Cd: 57.08 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e210-il-100000-n5.txt Download as CSV file: xf-e210-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E210 (13.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4156 0.07970 0.07508 -0.0533 1.0000 0.0303
-9.000 -0.4321 0.07512 0.07058 -0.0539 1.0000 0.0300
-8.750 -0.4578 0.07034 0.06588 -0.0546 1.0000 0.0298
-8.500 -0.4805 0.06407 0.05959 -0.0604 0.9953 0.0295
-8.250 -0.4801 0.05401 0.04906 -0.0749 0.9827 0.0294
-8.000 -0.4708 0.04704 0.04151 -0.0820 0.9723 0.0295
-7.750 -0.4560 0.04178 0.03562 -0.0858 0.9623 0.0298
-7.500 -0.4342 0.03758 0.03076 -0.0885 0.9539 0.0302
-7.250 -0.4065 0.03492 0.02789 -0.0909 0.9471 0.0314
-7.000 -0.3805 0.03326 0.02606 -0.0920 0.9383 0.0332
-6.750 -0.3478 0.03106 0.02349 -0.0943 0.9325 0.0349
-6.500 -0.3218 0.02901 0.02107 -0.0947 0.9230 0.0360
-6.250 -0.2867 0.02708 0.01879 -0.0965 0.9180 0.0374
-6.000 -0.2603 0.02560 0.01716 -0.0966 0.9081 0.0389
-5.750 -0.2275 0.02445 0.01599 -0.0981 0.9013 0.0419
-5.500 -0.1972 0.02335 0.01474 -0.0987 0.8927 0.0448
-5.250 -0.1653 0.02224 0.01347 -0.0995 0.8849 0.0474
-5.000 -0.1327 0.02110 0.01233 -0.1007 0.8769 0.0510
-4.750 -0.1008 0.02028 0.01140 -0.1016 0.8674 0.0579
-4.500 -0.0635 0.01930 0.01039 -0.1037 0.8603 0.0704
-4.250 -0.0314 0.01839 0.00956 -0.1049 0.8495 0.0918
-4.000 0.0044 0.01756 0.00884 -0.1068 0.8403 0.1341
-3.750 0.0400 0.01666 0.00824 -0.1089 0.8307 0.2114
-3.500 0.0721 0.01588 0.00787 -0.1102 0.8190 0.3120
-3.250 0.1057 0.01550 0.00770 -0.1113 0.8078 0.3967
-3.000 0.1408 0.01535 0.00750 -0.1124 0.7970 0.4550
-2.750 0.1740 0.01529 0.00732 -0.1132 0.7850 0.4955
-2.500 0.2047 0.01527 0.00721 -0.1135 0.7725 0.5257
-2.250 0.2352 0.01525 0.00710 -0.1137 0.7605 0.5502
-2.000 0.2664 0.01524 0.00696 -0.1141 0.7491 0.5728
-1.750 0.2972 0.01523 0.00685 -0.1144 0.7383 0.5921
-1.500 0.3249 0.01526 0.00679 -0.1142 0.7266 0.6097
-1.250 0.3532 0.01528 0.00673 -0.1140 0.7159 0.6268
-1.000 0.3824 0.01530 0.00665 -0.1141 0.7063 0.6430
-0.750 0.4092 0.01534 0.00662 -0.1138 0.6959 0.6579
-0.500 0.4366 0.01538 0.00660 -0.1135 0.6865 0.6727
-0.250 0.4645 0.01543 0.00655 -0.1134 0.6778 0.6875
0.000 0.4904 0.01549 0.00659 -0.1129 0.6684 0.7022
0.250 0.5185 0.01555 0.00656 -0.1128 0.6607 0.7169
0.500 0.5440 0.01562 0.00663 -0.1123 0.6516 0.7319
0.750 0.5711 0.01569 0.00665 -0.1120 0.6444 0.7477
1.000 0.5960 0.01576 0.00674 -0.1114 0.6361 0.7649
1.250 0.6220 0.01583 0.00678 -0.1108 0.6292 0.7842
1.500 0.6458 0.01591 0.00690 -0.1099 0.6213 0.8069
1.750 0.6708 0.01595 0.00693 -0.1091 0.6151 0.8338
2.000 0.6928 0.01599 0.00706 -0.1078 0.6073 0.8693
2.250 0.7228 0.01601 0.00708 -0.1080 0.6011 0.9211
2.500 0.7569 0.01614 0.00721 -0.1096 0.5934 1.0000
2.750 0.7858 0.01637 0.00736 -0.1101 0.5870 1.0000
3.000 0.8129 0.01664 0.00759 -0.1102 0.5802 1.0000
3.250 0.8401 0.01689 0.00780 -0.1103 0.5736 1.0000
3.500 0.8679 0.01716 0.00802 -0.1105 0.5677 1.0000
3.750 0.8934 0.01745 0.00833 -0.1103 0.5606 1.0000
4.000 0.9215 0.01771 0.00853 -0.1105 0.5551 1.0000
4.250 0.9460 0.01803 0.00890 -0.1100 0.5481 1.0000
4.500 0.9726 0.01831 0.00919 -0.1100 0.5419 1.0000
4.750 0.9984 0.01862 0.00952 -0.1097 0.5358 1.0000
5.000 1.0230 0.01894 0.00989 -0.1093 0.5290 1.0000
5.250 1.0507 0.01923 0.01017 -0.1094 0.5235 1.0000
5.500 1.0728 0.01959 0.01065 -0.1085 0.5159 1.0000
5.750 1.0992 0.01988 0.01094 -0.1084 0.5098 1.0000
6.000 1.1215 0.02024 0.01141 -0.1075 0.5022 1.0000
6.250 1.1466 0.02052 0.01174 -0.1071 0.4951 1.0000
6.500 1.1682 0.02087 0.01220 -0.1061 0.4869 1.0000
6.750 1.1927 0.02113 0.01248 -0.1056 0.4792 1.0000
7.000 1.2126 0.02149 0.01297 -0.1043 0.4701 1.0000
7.250 1.2360 0.02175 0.01329 -0.1035 0.4619 1.0000
7.500 1.2551 0.02210 0.01377 -0.1021 0.4521 1.0000
7.750 1.2748 0.02244 0.01421 -0.1008 0.4424 1.0000
8.000 1.2957 0.02270 0.01451 -0.0996 0.4328 1.0000
8.250 1.3119 0.02309 0.01506 -0.0977 0.4212 1.0000
8.500 1.3282 0.02347 0.01556 -0.0958 0.4095 1.0000
8.750 1.3437 0.02386 0.01604 -0.0938 0.3974 1.0000
9.000 1.3579 0.02428 0.01654 -0.0916 0.3845 1.0000
9.250 1.3690 0.02473 0.01706 -0.0889 0.3709 1.0000
9.500 1.3782 0.02527 0.01770 -0.0860 0.3566 1.0000
9.750 1.3858 0.02592 0.01842 -0.0830 0.3409 1.0000
10.000 1.3920 0.02668 0.01924 -0.0799 0.3238 1.0000
10.250 1.3963 0.02759 0.02018 -0.0767 0.3052 1.0000
10.500 1.3986 0.02868 0.02126 -0.0736 0.2861 1.0000
10.750 1.3992 0.02999 0.02258 -0.0705 0.2653 1.0000
11.000 1.3971 0.03158 0.02413 -0.0674 0.2450 1.0000
11.250 1.3933 0.03345 0.02599 -0.0646 0.2256 1.0000
11.500 1.3886 0.03559 0.02810 -0.0621 0.2071 1.0000
11.750 1.3826 0.03802 0.03051 -0.0599 0.1905 1.0000
12.000 1.3763 0.04069 0.03317 -0.0581 0.1755 1.0000
12.250 1.3700 0.04357 0.03606 -0.0567 0.1619 1.0000
12.500 1.3637 0.04662 0.03914 -0.0556 0.1494 1.0000
12.750 1.3574 0.04985 0.04241 -0.0548 0.1383 1.0000
13.000 1.3504 0.05330 0.04588 -0.0543 0.1286 1.0000
13.250 1.3446 0.05678 0.04941 -0.0540 0.1188 1.0000
13.500 1.3397 0.06028 0.05298 -0.0539 0.1101 1.0000
13.750 1.3326 0.06415 0.05686 -0.0540 0.1028 1.0000
14.000 1.3288 0.06776 0.06057 -0.0542 0.0948 1.0000
14.250 1.3231 0.07169 0.06453 -0.0546 0.0885 1.0000
14.500 1.3189 0.07554 0.06851 -0.0551 0.0819 1.0000
14.750 1.3136 0.07962 0.07262 -0.0558 0.0764 1.0000
15.000 1.3098 0.08362 0.07674 -0.0566 0.0704 1.0000
15.250 1.3035 0.08802 0.08114 -0.0576 0.0658 1.0000
15.500 1.3007 0.09207 0.08535 -0.0586 0.0601 1.0000
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Polar data table (+)
Polar graphs
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