E210 (13.64%) (e210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 100,000 Max Cl/Cd: 52.66 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e210-il-100000.txt Download as CSV file: xf-e210-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3797 0.09718 0.09301 -0.0348 1.0000 0.1366
-7.750 -0.4230 0.09667 0.09270 -0.0329 1.0000 0.1373
-7.500 -0.4620 0.09490 0.09109 -0.0337 1.0000 0.1376
-7.250 -0.4085 0.09101 0.08712 -0.0266 1.0000 0.1423
-7.000 -0.4250 0.08999 0.08620 -0.0232 1.0000 0.1443
-6.750 -0.4392 0.08786 0.08416 -0.0243 0.9972 0.1488
-6.500 -0.4190 0.08144 0.07773 -0.0350 0.9867 0.1570
-6.250 -0.4189 0.05007 0.04494 -0.0736 0.9697 0.0824
-6.000 -0.3867 0.04337 0.03764 -0.0786 0.9614 0.0732
-5.750 -0.3515 0.03833 0.03185 -0.0829 0.9532 0.0719
-5.500 -0.3098 0.03475 0.02765 -0.0869 0.9467 0.0728
-5.250 -0.2736 0.03192 0.02428 -0.0891 0.9376 0.0732
-5.000 -0.2281 0.02966 0.02156 -0.0925 0.9322 0.0762
-4.750 -0.1931 0.02805 0.01959 -0.0939 0.9220 0.0812
-4.500 -0.1499 0.02626 0.01782 -0.0967 0.9163 0.0874
-4.250 -0.1147 0.02487 0.01634 -0.0979 0.9067 0.0964
-4.000 -0.0780 0.02359 0.01521 -0.0996 0.8982 0.1158
-3.750 -0.0373 0.02179 0.01380 -0.1022 0.8914 0.1787
-3.500 -0.0024 0.02019 0.01302 -0.1044 0.8827 0.3182
-3.250 0.0384 0.01976 0.01309 -0.1063 0.8760 0.4779
-3.000 0.0709 0.01979 0.01312 -0.1063 0.8662 0.5361
-2.750 0.1139 0.01959 0.01287 -0.1080 0.8608 0.5821
-2.500 0.1454 0.01955 0.01278 -0.1078 0.8509 0.6158
-2.250 0.1871 0.01925 0.01241 -0.1093 0.8453 0.6484
-2.000 0.2153 0.01916 0.01229 -0.1085 0.8347 0.6722
-1.750 0.2576 0.01877 0.01180 -0.1102 0.8292 0.6983
-1.500 0.2826 0.01871 0.01172 -0.1091 0.8177 0.7178
-1.250 0.3146 0.01852 0.01145 -0.1091 0.8090 0.7383
-1.000 0.3473 0.01832 0.01115 -0.1095 0.8002 0.7590
-0.750 0.3715 0.01829 0.01108 -0.1083 0.7896 0.7765
-0.500 0.4065 0.01801 0.01071 -0.1089 0.7827 0.7947
-0.250 0.4259 0.01807 0.01076 -0.1070 0.7713 0.8122
0.000 0.4502 0.01804 0.01069 -0.1060 0.7621 0.8312
0.250 0.4786 0.01793 0.01050 -0.1057 0.7538 0.8521
0.500 0.4969 0.01798 0.01056 -0.1036 0.7439 0.8732
0.750 0.5279 0.01779 0.01029 -0.1037 0.7370 0.8985
1.000 0.5514 0.01786 0.01041 -0.1029 0.7268 0.9295
1.250 0.6057 0.01776 0.01021 -0.1081 0.7194 0.9624
1.500 0.6543 0.01788 0.01027 -0.1134 0.7096 1.0000
1.750 0.6816 0.01819 0.01046 -0.1147 0.7013 1.0000
2.000 0.7134 0.01846 0.01060 -0.1162 0.6932 1.0000
2.250 0.7406 0.01888 0.01095 -0.1167 0.6849 1.0000
2.500 0.7716 0.01916 0.01112 -0.1176 0.6774 1.0000
2.750 0.7963 0.01964 0.01157 -0.1175 0.6693 1.0000
3.000 0.8261 0.01994 0.01181 -0.1180 0.6621 1.0000
3.250 0.8500 0.02046 0.01232 -0.1176 0.6542 1.0000
3.500 0.8783 0.02080 0.01262 -0.1179 0.6470 1.0000
3.750 0.9026 0.02132 0.01316 -0.1175 0.6396 1.0000
4.000 0.9290 0.02173 0.01356 -0.1174 0.6322 1.0000
4.250 0.9545 0.02223 0.01406 -0.1172 0.6252 1.0000
4.500 0.9786 0.02271 0.01459 -0.1167 0.6174 1.0000
4.750 1.0062 0.02314 0.01502 -0.1168 0.6110 1.0000
5.000 1.0273 0.02373 0.01569 -0.1158 0.6027 1.0000
5.250 1.0577 0.02405 0.01599 -0.1162 0.5965 1.0000
5.500 1.0757 0.02475 0.01681 -0.1148 0.5877 1.0000
5.750 1.1073 0.02498 0.01702 -0.1153 0.5813 1.0000
6.000 1.1242 0.02568 0.01785 -0.1138 0.5721 1.0000
6.250 1.1531 0.02594 0.01815 -0.1138 0.5648 1.0000
6.500 1.1740 0.02643 0.01874 -0.1127 0.5556 1.0000
6.750 1.1976 0.02685 0.01923 -0.1119 0.5471 1.0000
7.000 1.2259 0.02696 0.01938 -0.1118 0.5385 1.0000
7.250 1.2438 0.02753 0.02009 -0.1102 0.5287 1.0000
7.500 1.2799 0.02729 0.01981 -0.1110 0.5204 1.0000
7.750 1.2952 0.02776 0.02046 -0.1089 0.5093 1.0000
8.000 1.3160 0.02803 0.02084 -0.1076 0.4987 1.0000
8.250 1.3466 0.02779 0.02061 -0.1075 0.4884 1.0000
8.500 1.3702 0.02774 0.02063 -0.1065 0.4766 1.0000
8.750 1.3869 0.02793 0.02096 -0.1044 0.4640 1.0000
9.000 1.4060 0.02795 0.02110 -0.1026 0.4511 1.0000
9.250 1.4253 0.02789 0.02113 -0.1008 0.4375 1.0000
9.500 1.4428 0.02784 0.02115 -0.0987 0.4230 1.0000
9.750 1.4571 0.02783 0.02123 -0.0962 0.4075 1.0000
10.000 1.4683 0.02790 0.02136 -0.0931 0.3909 1.0000
10.250 1.4766 0.02804 0.02157 -0.0897 0.3733 1.0000
10.500 1.4810 0.02827 0.02180 -0.0857 0.3551 1.0000
10.750 1.4762 0.02897 0.02258 -0.0806 0.3358 1.0000
11.000 1.4718 0.02982 0.02345 -0.0759 0.3147 1.0000
11.250 1.4659 0.03098 0.02457 -0.0715 0.2925 1.0000
11.500 1.4574 0.03255 0.02607 -0.0673 0.2697 1.0000
11.750 1.4476 0.03452 0.02795 -0.0636 0.2472 1.0000
12.000 1.4371 0.03685 0.03016 -0.0603 0.2264 1.0000
12.250 1.4269 0.03949 0.03266 -0.0576 0.2071 1.0000
12.500 1.4171 0.04236 0.03547 -0.0553 0.1889 1.0000
12.750 1.4087 0.04535 0.03839 -0.0535 0.1728 1.0000
13.000 1.4016 0.04842 0.04138 -0.0520 0.1581 1.0000
13.250 1.3957 0.05153 0.04446 -0.0509 0.1446 1.0000
13.500 1.3912 0.05464 0.04753 -0.0499 0.1323 1.0000
13.750 1.3876 0.05778 0.05063 -0.0491 0.1212 1.0000
14.000 1.3854 0.06084 0.05361 -0.0484 0.1107 1.0000
14.250 1.3806 0.06428 0.05711 -0.0482 0.1017 1.0000
14.500 1.3771 0.06775 0.06067 -0.0479 0.0931 1.0000
14.750 1.3763 0.07092 0.06377 -0.0477 0.0848 1.0000
15.000 1.3711 0.07472 0.06770 -0.0480 0.0780 1.0000
15.250 1.3698 0.07822 0.07124 -0.0479 0.0712 1.0000
15.500 1.3678 0.08174 0.07479 -0.0482 0.0654 1.0000
15.750 1.3671 0.08545 0.07862 -0.0483 0.0599 1.0000
16.000 1.3650 0.08921 0.08250 -0.0488 0.0556 1.0000
16.250 1.3720 0.09211 0.08541 -0.0484 0.0512 1.0000
16.500 1.3644 0.09687 0.09047 -0.0496 0.0488 1.0000
16.750 1.3590 0.10131 0.09509 -0.0508 0.0464 1.0000
17.000 1.3741 0.10322 0.09681 -0.0500 0.0427 1.0000
17.250 1.3609 0.10890 0.10283 -0.0521 0.0421 1.0000
17.500 1.3468 0.11500 0.10924 -0.0547 0.0416 1.0000
17.750 1.3315 0.12150 0.11603 -0.0577 0.0412 1.0000
18.000 1.3142 0.12858 0.12338 -0.0614 0.0410 1.0000
18.250 1.2942 0.13642 0.13148 -0.0660 0.0410 1.0000
18.500 1.2724 0.14500 0.14030 -0.0713 0.0412 1.0000
18.750 1.2489 0.15443 0.14994 -0.0775 0.0416 1.0000
19.000 1.2240 0.16482 0.16049 -0.0845 0.0421 1.0000
19.250 1.1997 0.17585 0.17161 -0.0919 0.0426 1.0000
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Polar data table (+)
Polar graphs
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