EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 200,000 Max Cl/Cd: 108.16 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e58-il-200000.txt Download as CSV file: xf-e58-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.4085 0.10751 0.10447 -0.0082 1.0000 0.0255
-6.250 -0.4142 0.10572 0.10272 -0.0063 1.0000 0.0260
-6.000 -0.4176 0.10381 0.10084 -0.0052 1.0000 0.0262
-5.750 -0.4175 0.10148 0.09851 -0.0050 1.0000 0.0268
-5.500 -0.4159 0.09898 0.09604 -0.0053 1.0000 0.0274
-5.250 -0.4123 0.09634 0.09342 -0.0062 1.0000 0.0280
-5.000 -0.4066 0.09349 0.09059 -0.0077 1.0000 0.0288
-4.750 -0.3980 0.09047 0.08758 -0.0100 1.0000 0.0296
-4.500 -0.3860 0.08724 0.08436 -0.0132 1.0000 0.0306
-4.250 -0.3629 0.08346 0.08057 -0.0198 0.9996 0.0322
-4.000 -0.2767 0.07711 0.07406 -0.0452 0.9945 0.0340
-3.750 -0.2081 0.06737 0.06423 -0.0621 0.9792 0.0356
-3.500 -0.1779 0.06416 0.06100 -0.0655 0.9738 0.0379
-3.250 -0.0662 0.05474 0.05121 -0.0949 0.9722 0.0480
-3.000 -0.0509 0.05279 0.04931 -0.0937 0.9653 0.0508
-2.750 0.0339 0.04609 0.04226 -0.1122 0.9644 0.0623
-2.500 0.0971 0.04202 0.03791 -0.1232 0.9627 0.0755
-2.000 0.2830 0.02691 0.02058 -0.1541 0.9718 0.0502
-1.750 0.3209 0.02564 0.01901 -0.1564 0.9677 0.0537
-1.500 0.3601 0.02467 0.01771 -0.1587 0.9650 0.0567
-1.250 0.3994 0.02410 0.01692 -0.1610 0.9624 0.0599
-1.000 0.4430 0.02345 0.01624 -0.1643 0.9602 0.0669
-0.750 0.4816 0.02321 0.01594 -0.1665 0.9558 0.0726
-0.500 0.5177 0.02291 0.01568 -0.1683 0.9502 0.0853
-0.250 0.5617 0.02270 0.01572 -0.1715 0.9469 0.1685
0.000 0.5940 0.02266 0.01574 -0.1725 0.9400 0.2130
0.250 0.6339 0.02251 0.01567 -0.1749 0.9351 0.2484
0.500 0.6831 0.02216 0.01555 -0.1791 0.9323 0.3122
0.750 0.7061 0.02068 0.01551 -0.1778 0.9234 1.0000
1.000 0.7546 0.02038 0.01505 -0.1814 0.9197 1.0000
1.250 0.7828 0.02028 0.01488 -0.1813 0.9108 1.0000
1.500 0.8243 0.02006 0.01462 -0.1838 0.9075 1.0000
1.750 0.8533 0.02001 0.01455 -0.1839 0.9002 1.0000
2.000 0.8914 0.01974 0.01428 -0.1856 0.8957 1.0000
2.250 0.9380 0.01916 0.01372 -0.1888 0.8929 1.0000
2.500 0.9661 0.01883 0.01346 -0.1884 0.8829 1.0000
2.750 1.0114 0.01814 0.01282 -0.1912 0.8799 1.0000
3.000 1.0372 0.01792 0.01267 -0.1904 0.8701 1.0000
3.250 1.0840 0.01694 0.01179 -0.1932 0.8665 1.0000
3.500 1.1169 0.01604 0.01102 -0.1932 0.8547 1.0000
3.750 1.1489 0.01515 0.01023 -0.1929 0.8421 1.0000
4.000 1.1795 0.01442 0.00961 -0.1924 0.8273 1.0000
4.250 1.2047 0.01405 0.00936 -0.1912 0.8070 1.0000
4.500 1.3001 0.01202 0.00662 -0.2019 0.6446 1.0000
4.750 1.3130 0.01319 0.00719 -0.1985 0.5439 1.0000
5.000 1.3180 0.01449 0.00793 -0.1939 0.4500 1.0000
5.250 1.3231 0.01589 0.00880 -0.1896 0.3602 1.0000
5.500 1.3286 0.01740 0.00970 -0.1856 0.2642 1.0000
5.750 1.3374 0.01908 0.01080 -0.1824 0.1633 1.0000
6.000 1.3429 0.02169 0.01260 -0.1787 0.0501 1.0000
6.250 1.3589 0.02303 0.01392 -0.1763 0.0352 1.0000
6.500 1.3750 0.02419 0.01512 -0.1741 0.0294 1.0000
6.750 1.3865 0.02586 0.01691 -0.1711 0.0272 1.0000
7.000 1.4005 0.02735 0.01854 -0.1684 0.0260 1.0000
7.250 1.4159 0.02910 0.02041 -0.1661 0.0249 1.0000
7.500 1.4359 0.03111 0.02257 -0.1645 0.0241 1.0000
7.750 1.4580 0.03287 0.02444 -0.1634 0.0223 1.0000
8.000 1.4853 0.03519 0.02685 -0.1634 0.0207 1.0000
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Polar data table (+)
Polar graphs
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