E471 (6.25%) (e471-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 100,000 Max Cl/Cd: 72.98 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e471-il-100000.txt Download as CSV file: xf-e471-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3793 0.09998 0.09555 -0.0212 1.0000 0.0639
-6.750 -0.3919 0.09915 0.09482 -0.0195 1.0000 0.0650
-6.500 -0.4003 0.09822 0.09398 -0.0216 1.0000 0.0660
-6.250 -0.4004 0.09676 0.09258 -0.0272 1.0000 0.0666
-6.000 -0.3965 0.09311 0.08899 -0.0305 1.0000 0.0672
-5.750 -0.3994 0.08905 0.08495 -0.0201 1.0000 0.0695
-5.500 -0.3967 0.08652 0.08246 -0.0184 1.0000 0.0729
-5.250 -0.3908 0.08383 0.07979 -0.0210 1.0000 0.0771
-5.000 -0.3617 0.07938 0.07527 -0.0378 1.0000 0.0810
-4.750 -0.3689 0.07661 0.07260 -0.0290 1.0000 0.0832
-4.500 -0.3600 0.07379 0.06978 -0.0288 1.0000 0.0868
-4.250 -0.3157 0.06812 0.06393 -0.0453 1.0000 0.0952
-4.000 -0.3138 0.06550 0.06136 -0.0408 1.0000 0.0977
-3.750 -0.2678 0.06045 0.05607 -0.0534 1.0000 0.1092
-3.500 -0.2604 0.05793 0.05362 -0.0505 1.0000 0.1128
-3.250 -0.2220 0.05367 0.04919 -0.0581 1.0000 0.1251
-3.000 -0.1697 0.05042 0.04555 -0.0687 1.0000 0.1496
-2.750 -0.1577 0.04715 0.04244 -0.0669 1.0000 0.1543
-2.500 -0.1251 0.04449 0.03966 -0.0708 1.0000 0.1812
-2.000 0.0043 0.03389 0.02771 -0.0910 1.0000 0.1387
-1.750 0.0854 0.02705 0.01893 -0.0990 1.0000 0.0676
-1.500 0.1179 0.02563 0.01717 -0.1001 1.0000 0.0659
-1.250 0.1495 0.02447 0.01572 -0.1009 1.0000 0.0658
-1.000 0.1798 0.02355 0.01464 -0.1017 1.0000 0.0681
-0.750 0.2071 0.02314 0.01422 -0.1021 1.0000 0.0776
-0.500 0.2470 0.02259 0.01371 -0.1046 0.9968 0.0899
-0.250 0.2967 0.02063 0.01346 -0.1090 0.9966 0.5470
0.000 0.3210 0.02016 0.01360 -0.1080 0.9883 1.0000
0.250 0.3622 0.02087 0.01394 -0.1112 0.9820 1.0000
0.500 0.3984 0.02139 0.01423 -0.1135 0.9736 1.0000
0.750 0.4354 0.02193 0.01459 -0.1158 0.9657 1.0000
1.000 0.4759 0.02245 0.01496 -0.1187 0.9583 1.0000
1.250 0.5095 0.02285 0.01526 -0.1204 0.9487 1.0000
1.500 0.5469 0.02326 0.01559 -0.1226 0.9402 1.0000
1.750 0.5882 0.02360 0.01587 -0.1255 0.9322 1.0000
2.000 0.6219 0.02388 0.01615 -0.1269 0.9217 1.0000
2.250 0.6586 0.02410 0.01638 -0.1287 0.9116 1.0000
2.500 0.7046 0.02414 0.01644 -0.1320 0.9036 1.0000
2.750 0.7422 0.02414 0.01651 -0.1337 0.8926 1.0000
3.000 0.7790 0.02408 0.01657 -0.1351 0.8808 1.0000
3.250 0.8183 0.02385 0.01645 -0.1367 0.8691 1.0000
3.500 0.8610 0.02338 0.01612 -0.1386 0.8574 1.0000
3.750 0.9098 0.02252 0.01550 -0.1411 0.8471 1.0000
4.000 0.9652 0.02119 0.01441 -0.1444 0.8374 1.0000
4.250 1.0119 0.01998 0.01344 -0.1459 0.8236 1.0000
4.500 1.0486 0.01904 0.01272 -0.1458 0.8045 1.0000
4.750 1.0919 0.01776 0.01173 -0.1463 0.7830 1.0000
5.000 1.1242 0.01695 0.01113 -0.1451 0.7519 1.0000
5.250 1.1525 0.01641 0.01072 -0.1434 0.7083 1.0000
5.500 1.1786 0.01615 0.01042 -0.1412 0.6423 1.0000
5.750 1.1982 0.01658 0.01048 -0.1381 0.5342 1.0000
6.000 1.2052 0.01813 0.01112 -0.1336 0.3953 1.0000
6.250 1.2082 0.02017 0.01223 -0.1295 0.2629 1.0000
6.500 1.2127 0.02258 0.01367 -0.1261 0.1412 1.0000
6.750 1.2131 0.02622 0.01652 -0.1214 0.0624 1.0000
7.000 1.2245 0.02860 0.01888 -0.1184 0.0495 1.0000
7.250 1.2414 0.03105 0.02132 -0.1164 0.0426 1.0000
7.500 1.2629 0.03302 0.02339 -0.1152 0.0371 1.0000
7.750 1.2929 0.03665 0.02704 -0.1154 0.0346 1.0000
8.000 1.3251 0.04139 0.03212 -0.1156 0.0338 1.0000
8.250 1.3480 0.04550 0.03667 -0.1144 0.0338 1.0000
8.500 1.3663 0.04956 0.04122 -0.1127 0.0341 1.0000
8.750 1.3804 0.05224 0.04442 -0.1100 0.0349 1.0000
9.000 1.3820 0.05701 0.05016 -0.1052 0.0377 1.0000
9.250 1.3779 0.06278 0.05658 -0.1012 0.0403 1.0000
9.500 1.3733 0.06820 0.06239 -0.0980 0.0423 1.0000
9.750 1.3717 0.07505 0.06940 -0.0962 0.0445 1.0000
10.000 1.2877 0.07488 0.06987 -0.0831 0.0459 1.0000
10.250 1.2550 0.07790 0.07323 -0.0777 0.0466 1.0000
10.500 1.2236 0.08232 0.07792 -0.0746 0.0468 1.0000
10.750 1.1919 0.08762 0.08347 -0.0730 0.0469 1.0000
11.000 1.1608 0.09334 0.08939 -0.0728 0.0469 1.0000
11.250 1.1307 0.09933 0.09557 -0.0739 0.0468 1.0000
11.500 1.0995 0.10549 0.10188 -0.0760 0.0466 1.0000
11.750 1.0677 0.11165 0.10817 -0.0790 0.0464 1.0000
12.000 1.0367 0.11904 0.11568 -0.0840 0.0463 1.0000
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Polar data table (+)
Polar graphs
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