E63 (4.25%) (e63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.67 at α=0° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e63-il-1000000-n5.txt Download as CSV file: xf-e63-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2028 0.08959 0.08787 -0.0594 0.9796 0.0047
-7.000 -0.1929 0.08670 0.08500 -0.0612 0.9767 0.0047
-6.750 -0.1796 0.08372 0.08202 -0.0640 0.9745 0.0047
-6.500 -0.1595 0.08001 0.07831 -0.0686 0.9731 0.0047
-6.250 -0.1362 0.07620 0.07450 -0.0740 0.9722 0.0047
-6.000 -0.1317 0.07376 0.07208 -0.0740 0.9656 0.0047
-5.750 -0.1087 0.07003 0.06835 -0.0793 0.9633 0.0047
-5.500 -0.0813 0.06608 0.06438 -0.0857 0.9618 0.0047
-5.250 -0.0506 0.06188 0.06017 -0.0929 0.9607 0.0047
-5.000 -0.0343 0.05882 0.05711 -0.0957 0.9549 0.0047
-4.750 -0.0027 0.05473 0.05300 -0.1026 0.9523 0.0047
-4.500 0.0350 0.05032 0.04856 -0.1109 0.9506 0.0047
-4.250 0.0777 0.04563 0.04383 -0.1201 0.9494 0.0047
-4.000 0.1245 0.04076 0.03889 -0.1298 0.9486 0.0047
-3.750 0.1748 0.03575 0.03379 -0.1398 0.9479 0.0047
-3.500 0.2122 0.03160 0.02951 -0.1455 0.9426 0.0047
-3.250 0.2788 0.02389 0.02150 -0.1591 0.9421 0.0042
-3.000 0.3424 0.01753 0.01469 -0.1691 0.9422 0.0036
-2.750 0.4020 0.01219 0.00869 -0.1768 0.9431 0.0031
-2.500 0.4479 0.00926 0.00518 -0.1808 0.9431 0.0030
-2.250 0.4843 0.00793 0.00357 -0.1826 0.9407 0.0034
-2.000 0.5177 0.00749 0.00307 -0.1838 0.9375 0.0045
-1.750 0.5545 0.00698 0.00249 -0.1858 0.9352 0.0053
-1.500 0.5863 0.00654 0.00197 -0.1867 0.9287 0.0074
-1.250 0.6262 0.00614 0.00145 -0.1892 0.9236 0.0084
-1.000 0.6652 0.00585 0.00112 -0.1917 0.9159 0.0238
-0.750 0.7135 0.00553 0.00091 -0.1965 0.9068 0.0783
-0.500 0.7649 0.00534 0.00076 -0.2020 0.8864 0.1413
-0.250 0.8030 0.00519 0.00077 -0.2045 0.8565 0.2734
0.000 0.8309 0.00527 0.00083 -0.2045 0.8189 0.3572
0.250 0.8544 0.00545 0.00095 -0.2036 0.7737 0.4395
0.750 0.9003 0.00584 0.00130 -0.2015 0.6792 0.6414
1.000 0.9237 0.00601 0.00152 -0.2007 0.6323 0.7648
1.250 0.9386 0.00599 0.00165 -0.1976 0.5874 0.9633
1.500 0.9619 0.00639 0.00182 -0.1967 0.5359 1.0000
1.750 0.9857 0.00679 0.00199 -0.1959 0.4867 1.0000
2.000 1.0097 0.00720 0.00217 -0.1952 0.4377 1.0000
2.250 1.0338 0.00761 0.00237 -0.1946 0.3919 1.0000
2.500 1.0576 0.00807 0.00259 -0.1938 0.3409 1.0000
2.750 1.0814 0.00855 0.00283 -0.1931 0.2905 1.0000
3.000 1.1056 0.00897 0.00314 -0.1925 0.2500 1.0000
3.250 1.1292 0.00948 0.00343 -0.1918 0.2032 1.0000
3.500 1.1521 0.01009 0.00377 -0.1910 0.1495 1.0000
3.750 1.1760 0.01056 0.00408 -0.1903 0.1143 1.0000
4.000 1.1995 0.01109 0.00444 -0.1895 0.0792 1.0000
4.250 1.2212 0.01190 0.00494 -0.1885 0.0293 1.0000
4.500 1.2450 0.01239 0.00534 -0.1878 0.0135 1.0000
4.750 1.2682 0.01299 0.00591 -0.1869 0.0017 1.0000
5.000 1.2927 0.01338 0.00637 -0.1862 0.0014 1.0000
5.250 1.3169 0.01382 0.00688 -0.1854 0.0013 1.0000
5.500 1.3406 0.01433 0.00749 -0.1845 0.0012 1.0000
5.750 1.3636 0.01497 0.00825 -0.1835 0.0012 1.0000
6.000 1.3859 0.01576 0.00917 -0.1822 0.0012 1.0000
6.250 1.4070 0.01674 0.01030 -0.1807 0.0012 1.0000
6.500 1.4270 0.01792 0.01164 -0.1790 0.0012 1.0000
6.750 1.4458 0.01936 0.01326 -0.1771 0.0012 1.0000
7.000 1.4638 0.02115 0.01527 -0.1749 0.0012 1.0000
7.250 1.4818 0.02328 0.01763 -0.1727 0.0013 1.0000
7.500 1.4997 0.02585 0.02049 -0.1705 0.0013 1.0000
7.750 1.5161 0.02903 0.02401 -0.1681 0.0014 1.0000
8.000 1.5305 0.03235 0.02777 -0.1653 0.0014 1.0000
8.250 1.5445 0.03492 0.03062 -0.1629 0.0013 1.0000
8.500 1.5581 0.03692 0.03284 -0.1607 0.0012 1.0000
8.750 1.5698 0.03904 0.03518 -0.1582 0.0011 1.0000
9.000 1.5717 0.04332 0.03986 -0.1540 0.0011 1.0000
9.250 1.5808 0.04494 0.04165 -0.1516 0.0010 1.0000
9.500 1.5778 0.04869 0.04570 -0.1472 0.0009 1.0000
9.750 1.5684 0.05210 0.04936 -0.1421 0.0009 1.0000
10.000 1.5453 0.05674 0.05429 -0.1353 0.0009 1.0000
10.250 1.5371 0.05917 0.05687 -0.1314 0.0009 1.0000
10.500 1.5108 0.06476 0.06272 -0.1266 0.0009 1.0000
10.750 1.4792 0.07168 0.06990 -0.1232 0.0009 1.0000
11.000 1.4429 0.08022 0.07868 -0.1222 0.0010 1.0000
11.250 1.4300 0.08502 0.08360 -0.1231 0.0009 1.0000
11.500 1.4074 0.09284 0.09158 -0.1261 0.0009 1.0000
11.750 1.3704 0.10645 0.10539 -0.1342 0.0010 1.0000
12.000 1.3630 0.11416 0.11319 -0.1404 0.0010 1.0000
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Polar data table (+)
Polar graphs
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