E63 (4.25%) (e63-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 200,000 Max Cl/Cd: 110.04 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e63-il-200000-n5.txt Download as CSV file: xf-e63-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E63 (4.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3714 0.11498 0.11161 -0.0175 1.0000 0.0125
-7.500 -0.3722 0.11289 0.10956 -0.0166 1.0000 0.0126
-7.250 -0.3744 0.11098 0.10769 -0.0154 1.0000 0.0126
-7.000 -0.3641 0.10791 0.10464 -0.0177 0.9978 0.0126
-6.750 -0.3484 0.10439 0.10106 -0.0215 0.9950 0.0126
-6.500 -0.3313 0.10064 0.09731 -0.0255 0.9918 0.0126
-6.250 -0.3123 0.09680 0.09348 -0.0299 0.9883 0.0126
-6.000 -0.2900 0.09268 0.08935 -0.0352 0.9851 0.0126
-5.750 -0.2670 0.08864 0.08530 -0.0406 0.9822 0.0127
-5.500 -0.2474 0.08485 0.08151 -0.0449 0.9777 0.0127
-5.250 -0.2215 0.08067 0.07732 -0.0509 0.9744 0.0127
-5.000 -0.1978 0.07460 0.07127 -0.0575 0.9721 0.0131
-4.750 -0.1810 0.07037 0.06705 -0.0607 0.9671 0.0135
-4.500 -0.1577 0.06642 0.06308 -0.0646 0.9638 0.0139
-4.250 -0.1254 0.06225 0.05889 -0.0711 0.9615 0.0144
-4.000 -0.0901 0.05807 0.05466 -0.0784 0.9588 0.0149
-3.750 -0.0542 0.05390 0.05043 -0.0856 0.9544 0.0152
-3.500 -0.0058 0.04907 0.04551 -0.0956 0.9522 0.0153
-3.250 0.0675 0.04220 0.03840 -0.1114 0.9518 0.0137
-3.000 0.1139 0.03842 0.03445 -0.1184 0.9507 0.0115
-2.750 0.1741 0.03311 0.02881 -0.1291 0.9507 0.0104
-2.500 0.2365 0.02805 0.02334 -0.1387 0.9514 0.0096
-2.250 0.2961 0.02363 0.01836 -0.1466 0.9526 0.0092
-2.000 0.3502 0.02020 0.01427 -0.1524 0.9541 0.0094
-1.750 0.3943 0.01825 0.01176 -0.1556 0.9536 0.0113
-1.500 0.4347 0.01673 0.00987 -0.1584 0.9525 0.0152
-1.250 0.4738 0.01557 0.00850 -0.1606 0.9510 0.0160
-1.000 0.5130 0.01473 0.00754 -0.1630 0.9493 0.0179
-0.750 0.5500 0.01419 0.00683 -0.1648 0.9468 0.0233
-0.500 0.5833 0.01358 0.00640 -0.1661 0.9419 0.0961
-0.250 0.6218 0.01277 0.00639 -0.1690 0.9390 0.3824
0.000 0.6574 0.01194 0.00637 -0.1706 0.9364 0.7202
0.250 0.6763 0.01139 0.00605 -0.1681 0.9276 1.0000
0.500 0.7124 0.01121 0.00577 -0.1696 0.9233 1.0000
0.750 0.7416 0.01112 0.00562 -0.1697 0.9146 1.0000
1.000 0.7774 0.01089 0.00531 -0.1711 0.9095 1.0000
1.250 0.8061 0.01080 0.00519 -0.1711 0.8992 1.0000
1.500 0.8379 0.01065 0.00502 -0.1717 0.8886 1.0000
1.750 0.8723 0.01044 0.00481 -0.1727 0.8773 1.0000
2.000 0.9092 0.01021 0.00463 -0.1743 0.8641 1.0000
2.250 0.9524 0.00992 0.00433 -0.1772 0.8461 1.0000
2.500 1.0035 0.00966 0.00404 -0.1819 0.8187 1.0000
2.750 1.0510 0.00960 0.00386 -0.1857 0.7762 1.0000
3.000 1.0861 0.00987 0.00390 -0.1869 0.7182 1.0000
3.250 1.1113 0.01039 0.00426 -0.1860 0.6522 1.0000
3.500 1.1313 0.01107 0.00461 -0.1841 0.5827 1.0000
3.750 1.1490 0.01186 0.00505 -0.1819 0.5094 1.0000
4.000 1.1664 0.01271 0.00556 -0.1798 0.4343 1.0000
4.250 1.1846 0.01358 0.00611 -0.1780 0.3635 1.0000
4.500 1.2033 0.01450 0.00672 -0.1764 0.2948 1.0000
4.750 1.2225 0.01547 0.00739 -0.1749 0.2271 1.0000
5.000 1.2423 0.01645 0.00821 -0.1736 0.1662 1.0000
5.250 1.2615 0.01758 0.00903 -0.1722 0.1069 1.0000
5.500 1.2809 0.01874 0.00995 -0.1709 0.0604 1.0000
5.750 1.2977 0.02036 0.01115 -0.1691 0.0151 1.0000
6.000 1.3163 0.02187 0.01274 -0.1672 0.0067 1.0000
6.250 1.3359 0.02316 0.01430 -0.1654 0.0055 1.0000
6.500 1.3540 0.02469 0.01609 -0.1634 0.0050 1.0000
6.750 1.3711 0.02649 0.01812 -0.1612 0.0046 1.0000
7.000 1.3883 0.02859 0.02045 -0.1590 0.0044 1.0000
7.250 1.4067 0.03102 0.02315 -0.1570 0.0042 1.0000
7.500 1.4260 0.03385 0.02632 -0.1552 0.0042 1.0000
7.750 1.4443 0.03713 0.03001 -0.1531 0.0041 1.0000
8.000 1.4595 0.04087 0.03425 -0.1506 0.0041 1.0000
8.250 1.4698 0.04508 0.03901 -0.1475 0.0042 1.0000
8.500 1.4745 0.04963 0.04410 -0.1438 0.0043 1.0000
8.750 1.4740 0.05432 0.04929 -0.1397 0.0044 1.0000
9.000 1.4667 0.05933 0.05477 -0.1350 0.0044 1.0000
9.250 1.4536 0.06380 0.05976 -0.1300 0.0045 1.0000
9.500 1.4361 0.06799 0.06425 -0.1250 0.0045 1.0000
9.750 1.4171 0.07243 0.06882 -0.1209 0.0046 1.0000
10.000 1.3974 0.07723 0.07386 -0.1179 0.0046 1.0000
10.250 1.3770 0.08247 0.07934 -0.1163 0.0046 1.0000
10.500 1.3548 0.08859 0.08568 -0.1164 0.0047 1.0000
10.750 1.3334 0.09537 0.09265 -0.1183 0.0047 1.0000
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Polar data table (+)
Polar graphs
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