E63 (4.25%) (e63-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 500,000 Max Cl/Cd: 159.98 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e63-il-500000-n5.txt Download as CSV file: xf-e63-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2521 0.09042 0.08811 -0.0460 0.9843 0.0066
-6.750 -0.2488 0.08807 0.08578 -0.0460 0.9793 0.0066
-6.500 -0.2360 0.08508 0.08281 -0.0487 0.9761 0.0068
-6.250 -0.2148 0.08135 0.07908 -0.0536 0.9742 0.0071
-6.000 -0.2003 0.07811 0.07584 -0.0567 0.9701 0.0074
-5.750 -0.1822 0.07475 0.07249 -0.0607 0.9661 0.0075
-5.500 -0.1560 0.07095 0.06868 -0.0668 0.9637 0.0081
-5.250 -0.1259 0.06697 0.06469 -0.0739 0.9621 0.0083
-5.000 -0.1072 0.06383 0.06155 -0.0776 0.9561 0.0087
-4.750 -0.0728 0.05986 0.05755 -0.0855 0.9533 0.0090
-4.500 -0.0309 0.05559 0.05324 -0.0951 0.9516 0.0093
-4.250 0.0117 0.05122 0.04880 -0.1040 0.9505 0.0094
-3.750 0.0902 0.04300 0.04044 -0.1188 0.9438 0.0096
-3.500 0.1391 0.03839 0.03573 -0.1278 0.9422 0.0096
-3.250 0.1911 0.03373 0.03092 -0.1367 0.9412 0.0097
-3.000 0.2438 0.02919 0.02618 -0.1449 0.9407 0.0097
-2.500 0.3619 0.01835 0.01450 -0.1635 0.9415 0.0062
-2.250 0.4181 0.01401 0.00945 -0.1695 0.9425 0.0048
-2.000 0.4592 0.01224 0.00727 -0.1723 0.9417 0.0046
-1.750 0.4973 0.01096 0.00570 -0.1744 0.9407 0.0049
-1.500 0.5339 0.01011 0.00471 -0.1763 0.9392 0.0056
-1.250 0.5698 0.00957 0.00411 -0.1780 0.9373 0.0077
-1.000 0.5976 0.00921 0.00371 -0.1779 0.9309 0.0091
-0.750 0.6318 0.00873 0.00315 -0.1791 0.9270 0.0094
-0.500 0.6680 0.00833 0.00265 -0.1808 0.9235 0.0102
-0.250 0.7010 0.00778 0.00246 -0.1821 0.9159 0.1582
0.000 0.7417 0.00712 0.00238 -0.1853 0.9114 0.4129
0.250 0.7795 0.00666 0.00233 -0.1876 0.9018 0.5986
0.500 0.8184 0.00597 0.00220 -0.1899 0.8899 0.8571
0.750 0.8624 0.00566 0.00190 -0.1933 0.8725 1.0000
1.000 0.9071 0.00567 0.00174 -0.1970 0.8411 1.0000
1.250 0.9402 0.00589 0.00173 -0.1979 0.7989 1.0000
1.500 0.9658 0.00621 0.00181 -0.1973 0.7540 1.0000
1.750 0.9882 0.00662 0.00199 -0.1960 0.7045 1.0000
2.000 1.0091 0.00709 0.00218 -0.1944 0.6504 1.0000
2.250 1.0297 0.00761 0.00241 -0.1928 0.5929 1.0000
2.500 1.0500 0.00820 0.00267 -0.1912 0.5281 1.0000
2.750 1.0663 0.00929 0.00310 -0.1890 0.4027 1.0000
3.000 1.0850 0.01039 0.00356 -0.1875 0.2842 1.0000
3.250 1.1062 0.01124 0.00403 -0.1865 0.2014 1.0000
3.500 1.1286 0.01196 0.00444 -0.1856 0.1400 1.0000
3.750 1.1513 0.01264 0.00486 -0.1847 0.0904 1.0000
4.000 1.1741 0.01331 0.00533 -0.1839 0.0498 1.0000
4.250 1.1963 0.01412 0.00592 -0.1829 0.0145 1.0000
4.500 1.2206 0.01454 0.00636 -0.1822 0.0121 1.0000
4.750 1.2451 0.01495 0.00688 -0.1815 0.0110 1.0000
5.000 1.2692 0.01541 0.00742 -0.1807 0.0100 1.0000
5.250 1.2928 0.01598 0.00809 -0.1798 0.0091 1.0000
5.500 1.3147 0.01685 0.00913 -0.1786 0.0079 1.0000
5.750 1.3359 0.01779 0.01020 -0.1772 0.0075 1.0000
6.000 1.3575 0.01862 0.01115 -0.1759 0.0074 1.0000
6.250 1.3781 0.01961 0.01226 -0.1745 0.0073 1.0000
6.500 1.3980 0.02077 0.01356 -0.1729 0.0072 1.0000
6.750 1.4174 0.02210 0.01505 -0.1712 0.0071 1.0000
7.000 1.4365 0.02369 0.01689 -0.1695 0.0071 1.0000
7.250 1.4564 0.02528 0.01866 -0.1680 0.0070 1.0000
7.500 1.4771 0.02650 0.02004 -0.1667 0.0066 1.0000
7.750 1.4974 0.02769 0.02140 -0.1654 0.0061 1.0000
8.000 1.5174 0.02867 0.02252 -0.1641 0.0054 1.0000
8.250 1.5374 0.02906 0.02300 -0.1631 0.0045 1.0000
8.500 1.5564 0.02969 0.02372 -0.1618 0.0040 1.0000
8.750 1.5734 0.03063 0.02476 -0.1604 0.0035 1.0000
9.000 1.5839 0.03353 0.02798 -0.1576 0.0030 1.0000
9.250 1.6028 0.03418 0.02881 -0.1562 0.0025 1.0000
9.500 1.6132 0.03688 0.03190 -0.1533 0.0020 1.0000
9.750 1.6225 0.03907 0.03438 -0.1505 0.0016 1.0000
10.000 1.6295 0.04097 0.03650 -0.1475 0.0014 1.0000
10.250 1.6342 0.04235 0.03805 -0.1441 0.0013 1.0000
10.500 1.6329 0.04471 0.04065 -0.1399 0.0013 1.0000
10.750 1.6228 0.04842 0.04471 -0.1349 0.0013 1.0000
11.000 1.6101 0.05230 0.04893 -0.1302 0.0012 1.0000
11.250 1.6035 0.05515 0.05198 -0.1269 0.0012 1.0000
11.500 1.5814 0.06041 0.05756 -0.1229 0.0011 1.0000
11.750 1.5592 0.06615 0.06362 -0.1202 0.0012 1.0000
12.000 1.5363 0.07225 0.06998 -0.1191 0.0011 1.0000
12.250 1.5093 0.07989 0.07789 -0.1196 0.0012 1.0000
12.500 1.4893 0.08700 0.08519 -0.1220 0.0011 1.0000
12.750 1.4645 0.09645 0.09485 -0.1266 0.0012 1.0000
13.000 1.4342 0.10936 0.10798 -0.1348 0.0012 1.0000
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Polar data table (+)
Polar graphs
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