E62 (5.62%) (e62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 1,000,000 Max Cl/Cd: 191.48 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e62-il-1000000.txt Download as CSV file: xf-e62-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E62 (5.62%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3886 0.13923 0.13757 -0.0193 1.0000 0.0055
-11.000 -0.3855 0.13653 0.13488 -0.0195 1.0000 0.0055
-10.750 -0.3830 0.13386 0.13223 -0.0198 1.0000 0.0055
-10.500 -0.3763 0.13074 0.12911 -0.0212 0.9997 0.0056
-10.250 -0.3642 0.12707 0.12544 -0.0244 0.9989 0.0056
-10.000 -0.3520 0.12337 0.12174 -0.0274 0.9979 0.0056
-9.750 -0.3394 0.11974 0.11811 -0.0305 0.9969 0.0056
-9.500 -0.3265 0.11617 0.11453 -0.0337 0.9960 0.0056
-9.250 -0.3131 0.11245 0.11080 -0.0371 0.9953 0.0056
-9.000 -0.3014 0.10903 0.10738 -0.0397 0.9938 0.0056
-8.750 -0.2893 0.10553 0.10388 -0.0425 0.9920 0.0056
-7.500 -0.2149 0.08625 0.08461 -0.0615 0.9851 0.0058
-7.250 -0.2084 0.08349 0.08186 -0.0621 0.9803 0.0058
-7.000 -0.1942 0.08036 0.07873 -0.0649 0.9772 0.0060
-6.750 -0.1727 0.07681 0.07518 -0.0698 0.9752 0.0061
-6.500 -0.1470 0.07285 0.07121 -0.0762 0.9738 0.0063
-6.250 -0.1190 0.06885 0.06720 -0.0833 0.9727 0.0066
-6.000 -0.1065 0.06577 0.06412 -0.0860 0.9657 0.0067
-5.750 -0.0767 0.06155 0.05989 -0.0936 0.9633 0.0071
-5.500 -0.0407 0.05692 0.05524 -0.1027 0.9618 0.0079
-5.250 0.0112 0.05128 0.04954 -0.1159 0.9608 0.0089
-5.000 0.0568 0.04589 0.04409 -0.1267 0.9600 0.0089
-4.500 0.1311 0.03389 0.03188 -0.1441 0.9505 0.0096
-4.250 0.1728 0.03022 0.02809 -0.1508 0.9496 0.0101
-4.000 0.2184 0.02583 0.02350 -0.1577 0.9489 0.0105
-3.750 0.2640 0.02163 0.01904 -0.1638 0.9482 0.0112
-3.500 0.2961 0.01846 0.01561 -0.1657 0.9431 0.0119
-3.250 0.3332 0.01600 0.01287 -0.1682 0.9402 0.0131
-3.000 0.3700 0.01521 0.01186 -0.1698 0.9380 0.0141
-2.750 0.4129 0.01135 0.00748 -0.1744 0.9366 0.0161
-2.500 0.4505 0.01043 0.00645 -0.1767 0.9347 0.0182
-2.250 0.4815 0.00867 0.00437 -0.1767 0.9275 0.0128
-2.000 0.5197 0.00738 0.00290 -0.1788 0.9237 0.0122
-1.750 0.5533 0.00689 0.00232 -0.1800 0.9166 0.0131
-1.500 0.5887 0.00656 0.00192 -0.1817 0.9088 0.0139
-1.250 0.6204 0.00627 0.00154 -0.1824 0.8973 0.0143
-1.000 0.6513 0.00604 0.00120 -0.1830 0.8852 0.0143
-0.750 0.6808 0.00592 0.00094 -0.1832 0.8720 0.0154
-0.500 0.7099 0.00569 0.00083 -0.1835 0.8583 0.0913
-0.250 0.7384 0.00540 0.00087 -0.1839 0.8450 0.2521
0.000 0.7663 0.00519 0.00095 -0.1841 0.8314 0.4048
0.250 0.7940 0.00466 0.00115 -0.1844 0.8175 0.7450
0.500 0.8121 0.00432 0.00118 -0.1820 0.8035 1.0000
0.750 0.8386 0.00443 0.00120 -0.1816 0.7902 1.0000
1.000 0.8650 0.00454 0.00124 -0.1813 0.7770 1.0000
1.250 0.8912 0.00467 0.00129 -0.1809 0.7630 1.0000
1.500 0.9172 0.00479 0.00134 -0.1805 0.7482 1.0000
1.750 0.9430 0.00493 0.00142 -0.1800 0.7329 1.0000
2.000 0.9687 0.00507 0.00150 -0.1795 0.7172 1.0000
2.250 0.9942 0.00523 0.00158 -0.1790 0.7006 1.0000
2.500 1.0194 0.00539 0.00168 -0.1784 0.6799 1.0000
2.750 1.0431 0.00563 0.00182 -0.1775 0.6489 1.0000
3.000 1.0619 0.00619 0.00202 -0.1756 0.5746 1.0000
3.250 1.0790 0.00703 0.00235 -0.1736 0.4700 1.0000
3.500 1.0978 0.00787 0.00273 -0.1720 0.3791 1.0000
3.750 1.1175 0.00866 0.00311 -0.1706 0.2966 1.0000
4.000 1.1368 0.00952 0.00355 -0.1692 0.2139 1.0000
4.250 1.1546 0.01057 0.00411 -0.1675 0.1204 1.0000
4.500 1.1708 0.01185 0.00485 -0.1656 0.0254 1.0000
4.750 1.1936 0.01239 0.00530 -0.1646 0.0096 1.0000
5.000 1.2180 0.01272 0.00568 -0.1639 0.0090 1.0000
5.250 1.2418 0.01311 0.00612 -0.1631 0.0085 1.0000
5.500 1.2651 0.01356 0.00665 -0.1623 0.0078 1.0000
5.750 1.2875 0.01412 0.00728 -0.1612 0.0071 1.0000
6.000 1.3088 0.01482 0.00805 -0.1599 0.0067 1.0000
6.250 1.3292 0.01561 0.00894 -0.1584 0.0064 1.0000
6.500 1.3488 0.01646 0.00989 -0.1568 0.0064 1.0000
6.750 1.3679 0.01736 0.01089 -0.1552 0.0064 1.0000
7.000 1.3866 0.01831 0.01193 -0.1534 0.0065 1.0000
7.250 1.4041 0.01941 0.01313 -0.1515 0.0065 1.0000
7.500 1.4207 0.02071 0.01452 -0.1495 0.0064 1.0000
7.750 1.4385 0.02201 0.01592 -0.1477 0.0064 1.0000
8.000 1.4571 0.02338 0.01742 -0.1460 0.0065 1.0000
8.250 1.4774 0.02587 0.02015 -0.1443 0.0072 1.0000
8.500 1.4995 0.03047 0.02517 -0.1428 0.0084 1.0000
8.750 1.5162 0.03355 0.02853 -0.1408 0.0084 1.0000
9.000 1.5307 0.03586 0.03107 -0.1385 0.0079 1.0000
9.250 1.5424 0.03817 0.03360 -0.1360 0.0075 1.0000
9.500 1.5510 0.04064 0.03630 -0.1332 0.0072 1.0000
9.750 1.5568 0.04311 0.03898 -0.1302 0.0069 1.0000
10.000 1.5594 0.04562 0.04168 -0.1269 0.0068 1.0000
10.250 1.5582 0.04812 0.04435 -0.1231 0.0066 1.0000
10.500 1.5499 0.05056 0.04695 -0.1183 0.0065 1.0000
10.750 1.5380 0.05340 0.04998 -0.1134 0.0064 1.0000
11.000 1.5248 0.05657 0.05334 -0.1091 0.0064 1.0000
11.250 1.5095 0.06014 0.05709 -0.1053 0.0063 1.0000
11.500 1.4914 0.06433 0.06146 -0.1023 0.0062 1.0000
11.750 1.4721 0.06896 0.06628 -0.1000 0.0062 1.0000
12.000 1.4530 0.07387 0.07137 -0.0987 0.0062 1.0000
12.250 1.4328 0.07938 0.07705 -0.0984 0.0062 1.0000
12.500 1.4122 0.08548 0.08333 -0.0993 0.0062 1.0000
12.750 1.3939 0.09173 0.08975 -0.1012 0.0062 1.0000
13.000 1.3716 0.09949 0.09767 -0.1045 0.0062 1.0000
13.250 1.3509 0.10793 0.10627 -0.1092 0.0062 1.0000
13.500 1.3297 0.11781 0.11632 -0.1156 0.0063 1.0000
13.750 1.3070 0.12987 0.12854 -0.1240 0.0064 1.0000
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Polar data table (+)
Polar graphs
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