E226 (10.19%) (e226-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 100,000 Max Cl/Cd: 45.26 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e226-il-100000.txt Download as CSV file: xf-e226-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6144 0.05331 0.04851 -0.0398 1.0000 0.0726
-8.500 -0.6669 0.05961 0.05445 -0.0380 1.0000 0.0710
-8.250 -0.6905 0.05168 0.04575 -0.0373 1.0000 0.0601
-8.000 -0.6852 0.04738 0.04125 -0.0363 1.0000 0.0589
-7.750 -0.6800 0.04345 0.03698 -0.0348 1.0000 0.0583
-7.500 -0.6718 0.03975 0.03291 -0.0331 1.0000 0.0572
-7.250 -0.6617 0.03616 0.02884 -0.0311 1.0000 0.0558
-7.000 -0.6487 0.03291 0.02511 -0.0291 1.0000 0.0546
-6.750 -0.6327 0.03020 0.02196 -0.0271 1.0000 0.0542
-6.500 -0.6142 0.02793 0.01937 -0.0254 1.0000 0.0546
-6.250 -0.5941 0.02600 0.01720 -0.0238 1.0000 0.0557
-6.000 -0.5735 0.02428 0.01531 -0.0222 1.0000 0.0577
-5.750 -0.5530 0.02297 0.01379 -0.0205 1.0000 0.0612
-5.500 -0.5353 0.02139 0.01235 -0.0189 1.0000 0.0675
-5.250 -0.5173 0.02007 0.01100 -0.0169 1.0000 0.0750
-5.000 -0.5019 0.01865 0.00973 -0.0147 1.0000 0.0908
-4.750 -0.4900 0.01657 0.00834 -0.0123 1.0000 0.1796
-4.500 -0.4743 0.01568 0.00787 -0.0107 1.0000 0.2692
-4.250 -0.4581 0.01515 0.00767 -0.0089 1.0000 0.3476
-4.000 -0.4414 0.01472 0.00749 -0.0071 1.0000 0.4136
-3.750 -0.4239 0.01435 0.00731 -0.0052 1.0000 0.4709
-3.500 -0.4061 0.01406 0.00719 -0.0033 1.0000 0.5265
-3.250 -0.3885 0.01383 0.00711 -0.0012 1.0000 0.5801
-3.000 -0.3712 0.01366 0.00710 0.0010 1.0000 0.6318
-2.750 -0.3545 0.01355 0.00713 0.0034 1.0000 0.6824
-2.500 -0.3383 0.01349 0.00719 0.0059 1.0000 0.7334
-2.250 -0.3229 0.01349 0.00729 0.0088 1.0000 0.7832
-2.000 -0.3075 0.01354 0.00743 0.0117 1.0000 0.8355
-1.750 -0.2841 0.01370 0.00763 0.0132 1.0000 0.8914
-1.500 -0.2289 0.01407 0.00789 0.0083 1.0000 0.9456
-1.250 -0.1493 0.01449 0.00809 -0.0019 1.0000 0.9821
-1.000 -0.0960 0.01458 0.00801 -0.0086 0.9985 1.0000
-0.750 -0.0407 0.01477 0.00805 -0.0154 0.9868 1.0000
-0.500 0.0124 0.01492 0.00808 -0.0214 0.9749 1.0000
-0.250 0.0643 0.01501 0.00809 -0.0270 0.9626 1.0000
0.000 0.1169 0.01505 0.00807 -0.0324 0.9504 1.0000
0.250 0.1742 0.01502 0.00801 -0.0384 0.9398 1.0000
0.500 0.2328 0.01486 0.00785 -0.0444 0.9291 1.0000
0.750 0.2804 0.01466 0.00767 -0.0481 0.9149 1.0000
1.000 0.3224 0.01444 0.00746 -0.0505 0.8994 1.0000
1.250 0.3552 0.01427 0.00730 -0.0510 0.8816 1.0000
1.500 0.3802 0.01418 0.00723 -0.0501 0.8616 1.0000
1.750 0.4049 0.01407 0.00711 -0.0487 0.8424 1.0000
2.000 0.4284 0.01396 0.00698 -0.0471 0.8238 1.0000
2.250 0.4474 0.01398 0.00700 -0.0448 0.8017 1.0000
2.500 0.4689 0.01394 0.00694 -0.0428 0.7812 1.0000
2.750 0.4894 0.01396 0.00695 -0.0407 0.7590 1.0000
3.000 0.5108 0.01397 0.00693 -0.0387 0.7368 1.0000
3.250 0.5318 0.01404 0.00698 -0.0368 0.7127 1.0000
3.500 0.5539 0.01410 0.00700 -0.0349 0.6891 1.0000
3.750 0.5753 0.01421 0.00708 -0.0331 0.6626 1.0000
4.000 0.5968 0.01435 0.00719 -0.0313 0.6350 1.0000
4.250 0.6185 0.01452 0.00731 -0.0296 0.6061 1.0000
4.500 0.6401 0.01472 0.00748 -0.0279 0.5758 1.0000
4.750 0.6616 0.01496 0.00765 -0.0262 0.5440 1.0000
5.000 0.6828 0.01525 0.00788 -0.0246 0.5101 1.0000
5.250 0.7035 0.01559 0.00818 -0.0229 0.4733 1.0000
5.500 0.7237 0.01599 0.00848 -0.0212 0.4348 1.0000
5.750 0.7433 0.01648 0.00883 -0.0196 0.3942 1.0000
6.000 0.7623 0.01706 0.00928 -0.0179 0.3511 1.0000
6.250 0.7806 0.01776 0.00985 -0.0162 0.3065 1.0000
6.500 0.7981 0.01861 0.01054 -0.0146 0.2613 1.0000
6.750 0.8145 0.01952 0.01127 -0.0129 0.2141 1.0000
7.000 0.8297 0.02047 0.01198 -0.0113 0.1662 1.0000
7.250 0.8435 0.02188 0.01313 -0.0095 0.1232 1.0000
7.500 0.8549 0.02384 0.01483 -0.0072 0.0845 1.0000
7.750 0.8694 0.02588 0.01679 -0.0052 0.0670 1.0000
8.000 0.8882 0.02778 0.01859 -0.0038 0.0595 1.0000
8.250 0.9108 0.03004 0.02100 -0.0027 0.0554 1.0000
8.500 0.9320 0.03194 0.02308 -0.0017 0.0513 1.0000
8.750 0.9526 0.03442 0.02551 -0.0011 0.0478 1.0000
9.000 0.9708 0.03726 0.02869 0.0001 0.0464 1.0000
9.250 0.9857 0.04016 0.03205 0.0018 0.0458 1.0000
9.500 0.9965 0.04338 0.03569 0.0035 0.0456 1.0000
9.750 1.0025 0.04693 0.03968 0.0055 0.0456 1.0000
10.000 1.0047 0.05070 0.04382 0.0075 0.0459 1.0000
10.250 1.0031 0.05468 0.04814 0.0094 0.0463 1.0000
10.500 0.9978 0.05904 0.05277 0.0111 0.0468 1.0000
10.750 0.9943 0.06374 0.05768 0.0123 0.0474 1.0000
11.000 0.9778 0.06554 0.05979 0.0153 0.0481 1.0000
11.250 0.9367 0.06965 0.06429 0.0164 0.0492 1.0000
11.500 0.8891 0.07695 0.07190 0.0125 0.0504 1.0000
11.750 0.8413 0.08780 0.08291 0.0041 0.0518 1.0000
12.000 0.7984 0.10242 0.09755 -0.0067 0.0546 1.0000
12.250 0.7851 0.11131 0.10640 -0.0112 0.0566 1.0000
12.500 0.7906 0.11464 0.10972 -0.0108 0.0579 1.0000
12.750 0.6191 0.13005 0.12543 -0.0170 0.0816 1.0000
13.000 0.6085 0.14343 0.13883 -0.0224 0.1218 1.0000
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Polar data table (+)
Polar graphs
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