E63 (4.25%) (e63-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 500,000 Max Cl/Cd: 176.79 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e63-il-500000.txt Download as CSV file: xf-e63-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3789 0.10888 0.10674 -0.0119 1.0000 0.0057
-7.500 -0.3792 0.10675 0.10462 -0.0111 1.0000 0.0058
-7.250 -0.3803 0.10473 0.10261 -0.0101 1.0000 0.0059
-7.000 -0.3701 0.10180 0.09969 -0.0124 0.9986 0.0060
-6.750 -0.3543 0.09847 0.09635 -0.0163 0.9960 0.0062
-6.500 -0.3405 0.09533 0.09322 -0.0197 0.9925 0.0064
-6.250 -0.3254 0.09205 0.08995 -0.0234 0.9886 0.0066
-6.000 -0.3020 0.08810 0.08599 -0.0292 0.9860 0.0068
-5.750 -0.2806 0.08426 0.08216 -0.0343 0.9821 0.0071
-5.500 -0.2581 0.08031 0.07820 -0.0397 0.9776 0.0075
-5.250 -0.2275 0.07602 0.07390 -0.0472 0.9750 0.0081
-5.000 -0.1801 0.07138 0.06923 -0.0601 0.9734 0.0089
-4.750 -0.1548 0.06774 0.06557 -0.0656 0.9668 0.0090
-4.500 -0.1122 0.06282 0.06062 -0.0757 0.9646 0.0091
-4.250 -0.0744 0.05570 0.05347 -0.0861 0.9632 0.0099
-4.000 -0.0387 0.05214 0.04985 -0.0924 0.9623 0.0108
-3.750 -0.0056 0.04866 0.04633 -0.0983 0.9574 0.0126
-3.500 0.0477 0.04385 0.04142 -0.1091 0.9558 0.0139
-3.250 0.1111 0.03912 0.03653 -0.1207 0.9552 0.0155
-3.000 0.1676 0.03530 0.03252 -0.1292 0.9545 0.0161
-2.750 0.2370 0.02774 0.02458 -0.1427 0.9562 0.0170
-2.500 0.2820 0.02481 0.02150 -0.1488 0.9556 0.0190
-2.250 0.3293 0.02227 0.01868 -0.1540 0.9552 0.0218
-2.000 0.3717 0.02156 0.01768 -0.1562 0.9537 0.0267
-1.250 0.5116 0.01393 0.00886 -0.1685 0.9548 0.0165
-1.000 0.5550 0.01204 0.00673 -0.1716 0.9547 0.0142
-0.750 0.5942 0.01132 0.00594 -0.1739 0.9531 0.0164
-0.500 0.6352 0.01057 0.00510 -0.1766 0.9518 0.0217
-0.250 0.6773 0.00977 0.00468 -0.1798 0.9507 0.1906
0.000 0.7107 0.00813 0.00480 -0.1813 0.9499 1.0000
0.250 0.7380 0.00799 0.00459 -0.1810 0.9428 1.0000
0.500 0.7753 0.00771 0.00425 -0.1828 0.9396 1.0000
0.750 0.8139 0.00738 0.00388 -0.1849 0.9373 1.0000
1.000 0.8413 0.00721 0.00369 -0.1845 0.9291 1.0000
1.250 0.8793 0.00685 0.00334 -0.1865 0.9248 1.0000
1.500 0.9101 0.00666 0.00314 -0.1868 0.9144 1.0000
1.750 0.9464 0.00645 0.00292 -0.1885 0.9038 1.0000
2.000 0.9897 0.00621 0.00268 -0.1917 0.8896 1.0000
2.250 1.0392 0.00605 0.00251 -0.1963 0.8658 1.0000
2.500 1.0802 0.00611 0.00242 -0.1990 0.8257 1.0000
2.750 1.1074 0.00656 0.00251 -0.1985 0.7529 1.0000
3.000 1.1208 0.00748 0.00281 -0.1950 0.6398 1.0000
3.250 1.1361 0.00835 0.00318 -0.1923 0.5431 1.0000
3.500 1.1542 0.00919 0.00358 -0.1903 0.4550 1.0000
3.750 1.1718 0.01023 0.00412 -0.1885 0.3484 1.0000
4.000 1.1914 0.01122 0.00463 -0.1871 0.2550 1.0000
4.250 1.2110 0.01230 0.00521 -0.1858 0.1627 1.0000
4.500 1.2304 0.01347 0.00590 -0.1844 0.0783 1.0000
4.750 1.2500 0.01471 0.00679 -0.1829 0.0201 1.0000
5.000 1.2735 0.01535 0.00752 -0.1819 0.0165 1.0000
5.250 1.2963 0.01609 0.00839 -0.1807 0.0151 1.0000
5.500 1.3180 0.01702 0.00945 -0.1793 0.0145 1.0000
5.750 1.3369 0.01836 0.01096 -0.1774 0.0136 1.0000
6.000 1.3544 0.02007 0.01283 -0.1752 0.0131 1.0000
6.250 1.3752 0.02129 0.01418 -0.1737 0.0129 1.0000
6.500 1.3961 0.02277 0.01580 -0.1721 0.0127 1.0000
6.750 1.4176 0.02465 0.01789 -0.1707 0.0123 1.0000
7.000 1.4402 0.02706 0.02051 -0.1693 0.0121 1.0000
7.250 1.4623 0.02858 0.02222 -0.1680 0.0111 1.0000
7.500 1.4835 0.03164 0.02561 -0.1663 0.0109 1.0000
7.750 1.5014 0.03564 0.03006 -0.1638 0.0108 1.0000
8.250 1.4719 0.03978 0.03563 -0.1474 0.0105 1.0000
8.500 1.4645 0.04698 0.04330 -0.1420 0.0111 1.0000
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Polar data table (+)
Polar graphs
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