E471 (6.25%) (e471-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 500,000 Max Cl/Cd: 138.49 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e471-il-500000-n5.txt Download as CSV file: xf-e471-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2170 0.09648 0.09427 -0.0504 0.9881 0.0072
-9.250 -0.2099 0.09217 0.08996 -0.0525 0.9867 0.0066
-8.750 -0.3003 0.10026 0.09796 -0.0443 0.9917 0.0063
-8.500 -0.2891 0.09655 0.09426 -0.0472 0.9895 0.0065
-8.250 -0.2786 0.09184 0.08956 -0.0510 0.9871 0.0057
-8.000 -0.2641 0.08847 0.08619 -0.0546 0.9851 0.0061
-7.750 -0.2485 0.08482 0.08251 -0.0587 0.9833 0.0065
-7.500 -0.2379 0.08150 0.07921 -0.0614 0.9792 0.0072
-7.250 -0.2260 0.07804 0.07575 -0.0649 0.9742 0.0083
-7.000 -0.2087 0.07375 0.07147 -0.0702 0.9709 0.0079
-6.750 -0.1921 0.06952 0.06724 -0.0758 0.9645 0.0089
-6.500 -0.1715 0.06486 0.06258 -0.0825 0.9601 0.0086
-6.250 -0.1424 0.05921 0.05690 -0.0921 0.9575 0.0086
-6.000 -0.1197 0.05401 0.05167 -0.0995 0.9501 0.0088
-5.750 -0.0817 0.04745 0.04504 -0.1110 0.9467 0.0091
-5.250 0.0063 0.03031 0.02738 -0.1364 0.9390 0.0107
-5.000 0.0353 0.02955 0.02656 -0.1386 0.9358 0.0121
-4.750 0.0784 0.02351 0.02006 -0.1455 0.9335 0.0124
-4.500 0.1247 0.01664 0.01228 -0.1516 0.9320 0.0112
-4.250 0.1587 0.01454 0.00979 -0.1536 0.9290 0.0113
-4.000 0.1897 0.01318 0.00817 -0.1546 0.9245 0.0117
-3.750 0.2227 0.01214 0.00692 -0.1559 0.9214 0.0125
-3.500 0.2565 0.01127 0.00585 -0.1573 0.9188 0.0134
-3.250 0.2870 0.01059 0.00504 -0.1580 0.9143 0.0140
-3.000 0.3179 0.01004 0.00438 -0.1587 0.9097 0.0147
-2.750 0.3501 0.00960 0.00387 -0.1597 0.9059 0.0157
-2.500 0.3806 0.00909 0.00328 -0.1603 0.9009 0.0156
-2.250 0.4113 0.00865 0.00275 -0.1609 0.8956 0.0155
-1.750 0.4719 0.00808 0.00202 -0.1619 0.8846 0.0154
-1.500 0.5022 0.00790 0.00176 -0.1624 0.8787 0.0154
-1.250 0.5308 0.00778 0.00156 -0.1625 0.8711 0.0156
-1.000 0.5602 0.00768 0.00138 -0.1627 0.8637 0.0160
-0.750 0.5882 0.00762 0.00127 -0.1627 0.8546 0.0169
-0.500 0.6171 0.00741 0.00120 -0.1629 0.8456 0.0755
-0.250 0.6465 0.00706 0.00122 -0.1635 0.8363 0.2251
0.000 0.6751 0.00676 0.00129 -0.1640 0.8260 0.3762
0.250 0.7034 0.00616 0.00150 -0.1644 0.8150 0.6831
0.500 0.7280 0.00596 0.00157 -0.1636 0.8035 0.8016
0.750 0.7456 0.00570 0.00153 -0.1608 0.7915 1.0000
1.000 0.7727 0.00580 0.00155 -0.1606 0.7776 1.0000
1.250 0.7995 0.00591 0.00158 -0.1603 0.7618 1.0000
1.500 0.8261 0.00603 0.00163 -0.1599 0.7450 1.0000
1.750 0.8523 0.00617 0.00169 -0.1595 0.7264 1.0000
2.000 0.8780 0.00634 0.00179 -0.1590 0.7039 1.0000
2.250 0.9030 0.00656 0.00189 -0.1584 0.6762 1.0000
2.500 0.9271 0.00683 0.00202 -0.1575 0.6411 1.0000
2.750 0.9498 0.00720 0.00218 -0.1565 0.5960 1.0000
3.000 0.9713 0.00768 0.00241 -0.1552 0.5407 1.0000
3.250 0.9923 0.00825 0.00273 -0.1539 0.4799 1.0000
3.500 1.0131 0.00889 0.00306 -0.1527 0.4156 1.0000
3.750 1.0290 0.01007 0.00359 -0.1508 0.2937 1.0000
4.000 1.0468 0.01116 0.00412 -0.1492 0.1899 1.0000
4.250 1.0678 0.01193 0.00456 -0.1482 0.1305 1.0000
4.500 1.0900 0.01256 0.00498 -0.1474 0.0902 1.0000
4.750 1.1109 0.01335 0.00550 -0.1463 0.0439 1.0000
5.000 1.1317 0.01417 0.00616 -0.1451 0.0107 1.0000
5.250 1.1554 0.01463 0.00664 -0.1444 0.0069 1.0000
5.500 1.1790 0.01509 0.00716 -0.1436 0.0059 1.0000
5.750 1.2023 0.01560 0.00775 -0.1427 0.0053 1.0000
6.000 1.2250 0.01616 0.00841 -0.1418 0.0049 1.0000
6.250 1.2471 0.01681 0.00916 -0.1407 0.0046 1.0000
6.500 1.2681 0.01759 0.01004 -0.1395 0.0043 1.0000
6.750 1.2855 0.01886 0.01153 -0.1376 0.0035 1.0000
7.000 1.3036 0.01999 0.01278 -0.1359 0.0033 1.0000
7.250 1.3232 0.02089 0.01378 -0.1345 0.0032 1.0000
7.500 1.3420 0.02190 0.01490 -0.1330 0.0030 1.0000
7.750 1.3601 0.02304 0.01616 -0.1313 0.0029 1.0000
8.000 1.3774 0.02433 0.01760 -0.1296 0.0027 1.0000
8.250 1.3942 0.02579 0.01922 -0.1278 0.0026 1.0000
8.500 1.4105 0.02743 0.02105 -0.1260 0.0024 1.0000
8.750 1.4261 0.02927 0.02309 -0.1240 0.0024 1.0000
9.000 1.4406 0.03131 0.02540 -0.1220 0.0023 1.0000
9.250 1.4531 0.03362 0.02798 -0.1198 0.0022 1.0000
9.500 1.4627 0.03609 0.03074 -0.1171 0.0022 1.0000
9.750 1.4672 0.03875 0.03369 -0.1138 0.0022 1.0000
10.000 1.4670 0.04153 0.03677 -0.1099 0.0022 1.0000
10.250 1.4628 0.04453 0.04007 -0.1058 0.0022 1.0000
10.500 1.4551 0.04779 0.04362 -0.1018 0.0022 1.0000
10.750 1.4441 0.05141 0.04753 -0.0980 0.0022 1.0000
11.000 1.4305 0.05539 0.05179 -0.0947 0.0022 1.0000
11.250 1.4139 0.05989 0.05656 -0.0920 0.0022 1.0000
11.500 1.3959 0.06482 0.06174 -0.0902 0.0022 1.0000
11.750 1.3769 0.07024 0.06739 -0.0896 0.0022 1.0000
12.000 1.3569 0.07628 0.07365 -0.0901 0.0023 1.0000
12.250 1.3355 0.08322 0.08079 -0.0920 0.0023 1.0000
12.500 1.3140 0.09104 0.08881 -0.0954 0.0023 1.0000
12.750 1.2933 0.09988 0.09782 -0.1005 0.0023 1.0000
13.000 1.2717 0.11062 0.10873 -0.1076 0.0023 1.0000
13.250 1.2523 0.12284 0.12111 -0.1160 0.0023 1.0000
13.500 1.2287 0.13916 0.13755 -0.1263 0.0024 1.0000
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Polar data table (+)
Polar graphs
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