E63 (4.25%) (e63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E63 (4.25%) (e63-il) Reynolds number: 1,000,000 Max Cl/Cd: 235.17 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e63-il-1000000.txt Download as CSV file: xf-e63-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1832 0.08151 0.07995 -0.0484 0.9855 0.0048
-7.500 -0.1700 0.07771 0.07615 -0.0516 0.9849 0.0049
-7.250 -0.1679 0.07487 0.07333 -0.0516 0.9799 0.0050
-7.000 -0.1577 0.07133 0.06979 -0.0538 0.9778 0.0050
-6.750 -0.1463 0.06763 0.06609 -0.0567 0.9761 0.0050
-6.500 -0.1336 0.06385 0.06232 -0.0599 0.9748 0.0050
-6.250 -0.1180 0.05986 0.05832 -0.0639 0.9736 0.0051
-6.000 -0.1135 0.05694 0.05542 -0.0646 0.9667 0.0051
-5.750 -0.0936 0.05261 0.05108 -0.0699 0.9647 0.0051
-5.500 -0.0702 0.04811 0.04658 -0.0760 0.9634 0.0051
-5.250 -0.0432 0.04335 0.04181 -0.0832 0.9625 0.0051
-4.250 0.0270 0.04700 0.04525 -0.1110 0.9572 0.0062
-4.000 0.0722 0.04268 0.04087 -0.1202 0.9555 0.0070
-3.750 0.1274 0.03805 0.03615 -0.1307 0.9547 0.0085
-3.500 0.1803 0.03399 0.03198 -0.1394 0.9541 0.0090
-3.250 0.2346 0.02943 0.02726 -0.1481 0.9538 0.0091
-3.000 0.2878 0.02508 0.02269 -0.1558 0.9536 0.0091
-2.750 0.3388 0.02122 0.01856 -0.1624 0.9535 0.0091
-1.250 0.5998 0.00822 0.00387 -0.1852 0.9520 0.0085
-1.000 0.6389 0.00737 0.00288 -0.1876 0.9512 0.0105
-0.750 0.6751 0.00696 0.00245 -0.1893 0.9501 0.0137
-0.500 0.7002 0.00673 0.00217 -0.1885 0.9437 0.0152
-0.250 0.7363 0.00608 0.00195 -0.1905 0.9406 0.2074
0.000 0.7753 0.00528 0.00200 -0.1935 0.9383 0.5852
0.250 0.8063 0.00477 0.00202 -0.1942 0.9319 0.8242
0.500 0.8399 0.00428 0.00172 -0.1952 0.9248 1.0000
0.750 0.8813 0.00414 0.00154 -0.1982 0.9133 1.0000
1.000 0.9300 0.00406 0.00139 -0.2029 0.8979 1.0000
1.250 0.9689 0.00412 0.00132 -0.2053 0.8693 1.0000
1.500 0.9981 0.00435 0.00135 -0.2055 0.8291 1.0000
1.750 1.0209 0.00470 0.00146 -0.2042 0.7809 1.0000
2.000 1.0411 0.00513 0.00162 -0.2024 0.7259 1.0000
2.250 1.0585 0.00575 0.00188 -0.2000 0.6472 1.0000
2.500 1.0748 0.00663 0.00221 -0.1976 0.5349 1.0000
2.750 1.0957 0.00732 0.00250 -0.1962 0.4522 1.0000
3.000 1.1158 0.00818 0.00286 -0.1949 0.3516 1.0000
3.250 1.1370 0.00898 0.00323 -0.1937 0.2643 1.0000
3.500 1.1589 0.00971 0.00360 -0.1928 0.1922 1.0000
3.750 1.1808 0.01048 0.00405 -0.1917 0.1241 1.0000
4.000 1.2018 0.01140 0.00458 -0.1906 0.0536 1.0000
4.250 1.2240 0.01220 0.00515 -0.1894 0.0131 1.0000
4.500 1.2488 0.01259 0.00561 -0.1888 0.0114 1.0000
4.750 1.2733 0.01303 0.00611 -0.1880 0.0106 1.0000
5.000 1.2974 0.01353 0.00671 -0.1872 0.0102 1.0000
5.250 1.3211 0.01407 0.00733 -0.1863 0.0096 1.0000
5.500 1.3443 0.01470 0.00805 -0.1853 0.0094 1.0000
5.750 1.3668 0.01543 0.00888 -0.1841 0.0091 1.0000
6.000 1.3885 0.01627 0.00982 -0.1828 0.0088 1.0000
6.250 1.4086 0.01739 0.01105 -0.1812 0.0083 1.0000
6.500 1.4254 0.01930 0.01317 -0.1788 0.0077 1.0000
6.750 1.4427 0.02183 0.01592 -0.1766 0.0069 1.0000
7.000 1.4656 0.02248 0.01665 -0.1757 0.0066 1.0000
7.250 1.4871 0.02379 0.01810 -0.1744 0.0063 1.0000
7.500 1.5081 0.02529 0.01975 -0.1730 0.0059 1.0000
7.750 1.5294 0.02586 0.02041 -0.1720 0.0051 1.0000
8.000 1.5503 0.02617 0.02075 -0.1711 0.0045 1.0000
8.250 1.5688 0.02708 0.02168 -0.1699 0.0040 1.0000
8.500 1.5791 0.03150 0.02656 -0.1667 0.0034 1.0000
8.750 1.5988 0.03204 0.02726 -0.1654 0.0031 1.0000
9.000 1.6137 0.03405 0.02952 -0.1631 0.0028 1.0000
9.250 1.6305 0.03491 0.03049 -0.1615 0.0024 1.0000
9.500 1.6400 0.03751 0.03337 -0.1586 0.0023 1.0000
9.750 1.6590 0.03709 0.03292 -0.1576 0.0020 1.0000
10.000 1.6775 0.03667 0.03246 -0.1565 0.0019 1.0000
10.250 1.6517 0.04347 0.03988 -0.1485 0.0016 1.0000
10.500 1.6647 0.04370 0.04018 -0.1461 0.0014 1.0000
10.750 1.6478 0.04787 0.04471 -0.1398 0.0014 1.0000
11.000 1.6296 0.05224 0.04940 -0.1342 0.0014 1.0000
11.250 1.6013 0.05808 0.05558 -0.1286 0.0013 1.0000
11.500 1.5757 0.06389 0.06168 -0.1248 0.0013 1.0000
11.750 1.5452 0.07078 0.06883 -0.1227 0.0013 1.0000
12.000 1.5238 0.07684 0.07508 -0.1225 0.0014 1.0000
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Polar data table (+)
Polar graphs
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