E62 (5.62%) (e62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E62 (5.62%) (e62-il) Reynolds number: 1,000,000 Max Cl/Cd: 164.57 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e62-il-1000000-n5.txt Download as CSV file: xf-e62-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1861 0.08836 0.08661 -0.0696 0.9811 0.0054
-7.750 -0.1750 0.08534 0.08360 -0.0718 0.9785 0.0054
-7.500 -0.1613 0.08207 0.08033 -0.0749 0.9763 0.0054
-7.250 -0.1457 0.07865 0.07692 -0.0786 0.9745 0.0054
-7.000 -0.1267 0.07488 0.07315 -0.0835 0.9730 0.0054
-6.750 -0.1218 0.07236 0.07065 -0.0839 0.9662 0.0054
-6.500 -0.1011 0.06860 0.06688 -0.0891 0.9633 0.0054
-6.250 -0.0759 0.06454 0.06281 -0.0955 0.9614 0.0054
-6.000 -0.0626 0.06126 0.05952 -0.0985 0.9545 0.0054
-5.750 -0.0370 0.05701 0.05525 -0.1049 0.9505 0.0054
-5.500 -0.0078 0.05236 0.05058 -0.1126 0.9481 0.0052
-5.250 0.0128 0.04847 0.04666 -0.1173 0.9390 0.0050
-5.000 0.0600 0.04281 0.04093 -0.1282 0.9363 0.0055
-3.500 0.3411 0.01171 0.00787 -0.1748 0.9116 0.0057
-3.250 0.3762 0.01075 0.00667 -0.1766 0.9045 0.0056
-3.000 0.4106 0.00985 0.00553 -0.1781 0.8960 0.0055
-2.750 0.4424 0.00896 0.00443 -0.1791 0.8857 0.0055
-2.500 0.4738 0.00788 0.00313 -0.1800 0.8752 0.0056
-2.250 0.5042 0.00712 0.00219 -0.1806 0.8639 0.0061
-2.000 0.5328 0.00686 0.00185 -0.1808 0.8517 0.0067
-1.750 0.5606 0.00670 0.00160 -0.1808 0.8382 0.0074
-1.500 0.5879 0.00658 0.00138 -0.1807 0.8231 0.0080
-1.250 0.6147 0.00654 0.00125 -0.1804 0.8078 0.0088
-1.000 0.6415 0.00649 0.00111 -0.1802 0.7936 0.0092
-0.750 0.6682 0.00645 0.00097 -0.1799 0.7792 0.0093
-0.500 0.6948 0.00644 0.00084 -0.1795 0.7645 0.0102
-0.250 0.7213 0.00646 0.00078 -0.1792 0.7511 0.0139
0.000 0.7482 0.00640 0.00079 -0.1790 0.7375 0.0620
0.250 0.7752 0.00625 0.00085 -0.1791 0.7219 0.1777
0.500 0.8024 0.00609 0.00096 -0.1792 0.7062 0.3261
0.750 0.8298 0.00589 0.00110 -0.1794 0.6909 0.5042
1.000 0.8565 0.00581 0.00122 -0.1793 0.6748 0.6243
1.250 0.8815 0.00558 0.00139 -0.1788 0.6564 0.8272
1.500 0.9002 0.00547 0.00142 -0.1766 0.6357 1.0000
1.750 0.9253 0.00568 0.00151 -0.1760 0.6095 1.0000
2.000 0.9500 0.00593 0.00164 -0.1754 0.5797 1.0000
2.250 0.9742 0.00622 0.00177 -0.1747 0.5448 1.0000
2.500 0.9962 0.00673 0.00198 -0.1736 0.4828 1.0000
2.750 1.0139 0.00770 0.00238 -0.1718 0.3685 1.0000
3.000 1.0335 0.00855 0.00275 -0.1704 0.2745 1.0000
3.250 1.0512 0.00963 0.00326 -0.1688 0.1602 1.0000
3.750 1.0927 0.01120 0.00414 -0.1664 0.0290 1.0000
4.000 1.1161 0.01168 0.00450 -0.1656 0.0085 1.0000
4.250 1.1412 0.01196 0.00480 -0.1651 0.0063 1.0000
4.500 1.1661 0.01226 0.00515 -0.1645 0.0054 1.0000
4.750 1.1907 0.01257 0.00550 -0.1639 0.0052 1.0000
5.000 1.2150 0.01291 0.00587 -0.1633 0.0051 1.0000
5.250 1.2391 0.01326 0.00625 -0.1626 0.0049 1.0000
5.500 1.2628 0.01364 0.00669 -0.1619 0.0046 1.0000
5.750 1.2860 0.01408 0.00718 -0.1610 0.0044 1.0000
6.000 1.3089 0.01456 0.00771 -0.1601 0.0042 1.0000
6.250 1.3313 0.01508 0.00828 -0.1592 0.0040 1.0000
6.500 1.3532 0.01564 0.00890 -0.1581 0.0038 1.0000
6.750 1.3746 0.01624 0.00959 -0.1570 0.0036 1.0000
7.000 1.3955 0.01688 0.01029 -0.1558 0.0034 1.0000
7.250 1.4158 0.01758 0.01105 -0.1545 0.0032 1.0000
7.500 1.4349 0.01839 0.01193 -0.1530 0.0031 1.0000
7.750 1.4522 0.01940 0.01304 -0.1511 0.0029 1.0000
8.000 1.4669 0.02074 0.01449 -0.1489 0.0028 1.0000
8.250 1.4793 0.02246 0.01636 -0.1462 0.0027 1.0000
8.500 1.4923 0.02434 0.01839 -0.1437 0.0027 1.0000
8.750 1.5058 0.02652 0.02074 -0.1414 0.0026 1.0000
9.000 1.5205 0.02860 0.02299 -0.1394 0.0026 1.0000
9.250 1.5348 0.03060 0.02519 -0.1374 0.0026 1.0000
9.500 1.5479 0.03229 0.02706 -0.1352 0.0026 1.0000
9.750 1.5582 0.03342 0.02833 -0.1325 0.0026 1.0000
10.000 1.5659 0.03475 0.02982 -0.1294 0.0025 1.0000
10.250 1.5715 0.03637 0.03161 -0.1261 0.0025 1.0000
10.500 1.5767 0.03784 0.03324 -0.1230 0.0025 1.0000
10.750 1.5793 0.03975 0.03533 -0.1197 0.0024 1.0000
11.000 1.5773 0.04233 0.03813 -0.1160 0.0024 1.0000
11.250 1.5745 0.04489 0.04089 -0.1126 0.0024 1.0000
11.500 1.5686 0.04783 0.04404 -0.1093 0.0024 1.0000
11.750 1.5594 0.05124 0.04768 -0.1062 0.0024 1.0000
12.000 1.5472 0.05514 0.05180 -0.1034 0.0024 1.0000
12.250 1.5357 0.05907 0.05595 -0.1014 0.0024 1.0000
12.500 1.5227 0.06345 0.06052 -0.1000 0.0024 1.0000
12.750 1.5079 0.06837 0.06564 -0.0993 0.0023 1.0000
13.000 1.4909 0.07400 0.07146 -0.0995 0.0023 1.0000
13.250 1.4740 0.08010 0.07774 -0.1006 0.0023 1.0000
13.500 1.4491 0.08825 0.08609 -0.1032 0.0024 1.0000
13.750 1.4337 0.09531 0.09331 -0.1064 0.0023 1.0000
14.000 1.4091 0.10530 0.10348 -0.1117 0.0024 1.0000
14.250 1.3906 0.11492 0.11326 -0.1176 0.0024 1.0000
14.500 1.3689 0.12656 0.12504 -0.1252 0.0024 1.0000
14.750 1.3476 0.13930 0.13792 -0.1336 0.0024 1.0000
15.000 1.3206 0.15531 0.15407 -0.1438 0.0025 1.0000
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Polar data table (+)
Polar graphs
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