E211 (10.96%) (e211-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 50,000 Max Cl/Cd: 37.86 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e211-il-50000.txt Download as CSV file: xf-e211-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4156 0.11768 0.11057 -0.0236 1.0000 0.2467
-9.250 -0.3987 0.11293 0.10582 -0.0225 1.0000 0.2539
-9.000 -0.4238 0.11275 0.10581 -0.0232 1.0000 0.2625
-8.750 -0.3965 0.10733 0.10034 -0.0215 1.0000 0.2726
-8.500 -0.3976 0.10443 0.09752 -0.0209 1.0000 0.2814
-8.250 -0.4218 0.10409 0.09735 -0.0205 1.0000 0.2921
-8.000 -0.4043 0.09994 0.09318 -0.0189 1.0000 0.3056
-7.750 -0.3950 0.09653 0.08980 -0.0174 1.0000 0.3186
-7.500 -0.3906 0.09350 0.08683 -0.0160 1.0000 0.3312
-6.500 -0.5140 0.06381 0.05724 -0.0457 1.0000 0.1437
-6.250 -0.5086 0.05723 0.05034 -0.0480 1.0000 0.1280
-6.000 -0.4999 0.05098 0.04359 -0.0503 1.0000 0.1181
-5.750 -0.4839 0.04652 0.03860 -0.0513 1.0000 0.1137
-5.500 -0.4658 0.04274 0.03437 -0.0518 1.0000 0.1132
-5.250 -0.4445 0.03930 0.03036 -0.0523 1.0000 0.1139
-5.000 -0.4208 0.03627 0.02675 -0.0525 1.0000 0.1150
-4.750 -0.3961 0.03345 0.02348 -0.0523 1.0000 0.1167
-4.500 -0.3726 0.03120 0.02111 -0.0518 1.0000 0.1212
-4.250 -0.3472 0.02934 0.01887 -0.0512 1.0000 0.1312
-4.000 -0.3236 0.02764 0.01721 -0.0503 1.0000 0.1477
-3.750 -0.3003 0.02595 0.01564 -0.0493 1.0000 0.1775
-3.500 -0.2776 0.02404 0.01426 -0.0487 1.0000 0.2573
-3.250 -0.2564 0.02173 0.01351 -0.0472 1.0000 0.4517
-3.000 -0.2519 0.02207 0.01454 -0.0402 1.0000 0.6202
-2.750 -0.2504 0.02251 0.01510 -0.0328 1.0000 0.6965
-2.500 -0.2502 0.02273 0.01534 -0.0257 1.0000 0.7546
-2.250 -0.2516 0.02272 0.01533 -0.0185 1.0000 0.8032
-2.000 -0.2527 0.02251 0.01510 -0.0117 1.0000 0.8517
-1.750 -0.2472 0.02219 0.01471 -0.0064 1.0000 0.9066
-1.500 -0.1291 0.02268 0.01455 -0.0220 1.0000 1.0000
-1.250 -0.1411 0.02212 0.01395 -0.0188 1.0000 1.0000
-1.000 -0.1346 0.02187 0.01352 -0.0185 1.0000 1.0000
-0.750 -0.1148 0.02197 0.01339 -0.0201 1.0000 1.0000
-0.500 -0.0904 0.02227 0.01345 -0.0223 1.0000 1.0000
-0.250 -0.0652 0.02271 0.01367 -0.0244 1.0000 1.0000
0.000 -0.0404 0.02326 0.01398 -0.0263 1.0000 1.0000
0.250 -0.0166 0.02388 0.01440 -0.0279 1.0000 1.0000
0.500 0.0063 0.02456 0.01491 -0.0293 1.0000 1.0000
0.750 0.0379 0.02555 0.01573 -0.0322 0.9957 1.0000
1.000 0.0877 0.02694 0.01693 -0.0383 0.9819 1.0000
1.250 0.1325 0.02811 0.01796 -0.0432 0.9678 1.0000
1.500 0.1752 0.02916 0.01890 -0.0476 0.9536 1.0000
1.750 0.2155 0.03013 0.01979 -0.0515 0.9398 1.0000
2.000 0.2548 0.03106 0.02066 -0.0550 0.9259 1.0000
2.250 0.2932 0.03194 0.02151 -0.0582 0.9120 1.0000
2.500 0.3304 0.03280 0.02235 -0.0611 0.8980 1.0000
2.750 0.3669 0.03363 0.02319 -0.0637 0.8839 1.0000
3.000 0.4025 0.03444 0.02404 -0.0661 0.8698 1.0000
3.250 0.4374 0.03524 0.02488 -0.0683 0.8555 1.0000
3.500 0.4720 0.03601 0.02571 -0.0702 0.8408 1.0000
3.750 0.5061 0.03676 0.02656 -0.0720 0.8260 1.0000
4.000 0.5404 0.03746 0.02736 -0.0736 0.8107 1.0000
4.250 0.5754 0.03808 0.02809 -0.0751 0.7948 1.0000
4.500 0.6124 0.03856 0.02875 -0.0765 0.7786 1.0000
4.750 0.6529 0.03880 0.02916 -0.0781 0.7623 1.0000
5.000 0.6996 0.03860 0.02918 -0.0800 0.7457 1.0000
5.250 0.7328 0.03877 0.02957 -0.0801 0.7267 1.0000
5.500 0.7715 0.03850 0.02953 -0.0804 0.7070 1.0000
5.750 0.8436 0.03620 0.02763 -0.0831 0.6874 1.0000
6.000 0.8846 0.03529 0.02702 -0.0826 0.6631 1.0000
6.250 0.9413 0.03316 0.02520 -0.0828 0.6356 1.0000
6.500 0.9879 0.03148 0.02377 -0.0820 0.6025 1.0000
6.750 1.0282 0.03005 0.02247 -0.0804 0.5636 1.0000
7.000 1.0561 0.02923 0.02168 -0.0775 0.5182 1.0000
7.250 1.0780 0.02868 0.02100 -0.0740 0.4652 1.0000
7.500 1.0907 0.02881 0.02089 -0.0697 0.4061 1.0000
7.750 1.0990 0.02968 0.02133 -0.0653 0.3456 1.0000
8.000 1.1063 0.03119 0.02241 -0.0615 0.2898 1.0000
8.250 1.1154 0.03328 0.02415 -0.0583 0.2406 1.0000
8.500 1.1254 0.03567 0.02621 -0.0554 0.1973 1.0000
8.750 1.1346 0.03809 0.02817 -0.0530 0.1601 1.0000
9.000 1.1464 0.04083 0.03081 -0.0508 0.1313 1.0000
9.250 1.1632 0.04389 0.03409 -0.0491 0.1123 1.0000
9.500 1.1855 0.04762 0.03801 -0.0482 0.1013 1.0000
9.750 1.2088 0.05127 0.04171 -0.0478 0.0934 1.0000
10.000 1.2137 0.05493 0.04591 -0.0452 0.0899 1.0000
10.250 1.2142 0.05850 0.04998 -0.0423 0.0873 1.0000
10.500 1.2122 0.06224 0.05414 -0.0395 0.0856 1.0000
10.750 1.2047 0.06618 0.05846 -0.0366 0.0850 1.0000
11.000 1.1893 0.07004 0.06267 -0.0333 0.0853 1.0000
11.250 1.1687 0.07408 0.06701 -0.0303 0.0857 1.0000
11.500 1.1446 0.07848 0.07168 -0.0283 0.0865 1.0000
11.750 1.1185 0.08344 0.07687 -0.0277 0.0874 1.0000
12.000 1.0915 0.08912 0.08274 -0.0285 0.0885 1.0000
12.250 1.0643 0.09566 0.08941 -0.0308 0.0897 1.0000
12.500 1.0409 0.10285 0.09670 -0.0340 0.0909 1.0000
12.750 1.0249 0.11013 0.10403 -0.0372 0.0919 1.0000
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Polar data table (+)
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