EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 500,000 Max Cl/Cd: 175.11 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e58-il-500000.txt Download as CSV file: xf-e58-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1845 0.09231 0.09000 -0.0726 0.9599 0.0156
-7.000 -0.1698 0.08946 0.08715 -0.0764 0.9586 0.0157
-6.750 -0.1854 0.08853 0.08626 -0.0713 0.9508 0.0158
-6.500 -0.1689 0.08504 0.08277 -0.0754 0.9484 0.0158
-6.250 -0.1476 0.08096 0.07868 -0.0809 0.9469 0.0159
-6.000 -0.1228 0.07695 0.07466 -0.0870 0.9458 0.0159
-5.750 -0.1330 0.07553 0.07327 -0.0836 0.9380 0.0159
-5.500 -0.1246 0.07030 0.06806 -0.0858 0.9359 0.0167
-5.250 -0.1003 0.06698 0.06472 -0.0903 0.9345 0.0171
-5.000 -0.0709 0.06339 0.06111 -0.0963 0.9335 0.0178
-4.750 -0.0603 0.06082 0.05854 -0.0980 0.9279 0.0183
-4.500 -0.0279 0.05673 0.05439 -0.1053 0.9245 0.0195
-4.250 0.0381 0.05083 0.04838 -0.1213 0.9233 0.0229
-3.250 0.3460 0.02017 0.01555 -0.1858 0.9329 0.0235
-3.000 0.3922 0.01735 0.01233 -0.1910 0.9332 0.0273
-2.750 0.4335 0.01635 0.01114 -0.1939 0.9329 0.0303
-2.500 0.4568 0.01585 0.01051 -0.1930 0.9282 0.0322
-2.250 0.4939 0.01497 0.00948 -0.1949 0.9258 0.0360
-2.000 0.5345 0.01410 0.00854 -0.1976 0.9244 0.0391
-1.750 0.5737 0.01354 0.00795 -0.1999 0.9232 0.0428
-1.500 0.6159 0.01293 0.00730 -0.2027 0.9221 0.0461
-1.250 0.6574 0.01240 0.00671 -0.2054 0.9212 0.0486
-1.000 0.6989 0.01190 0.00622 -0.2081 0.9205 0.0566
-0.750 0.7398 0.01140 0.00596 -0.2109 0.9201 0.1427
-0.500 0.7792 0.01107 0.00571 -0.2133 0.9196 0.1740
-0.250 0.7919 0.01121 0.00588 -0.2101 0.9125 0.1866
0.000 0.8302 0.01080 0.00556 -0.2122 0.9111 0.2098
0.500 0.9166 0.00922 0.00505 -0.2190 0.9088 0.6416
0.750 0.9450 0.00826 0.00470 -0.2185 0.9069 1.0000
1.000 0.9699 0.00822 0.00464 -0.2177 0.9018 1.0000
1.250 0.9997 0.00807 0.00448 -0.2179 0.8976 1.0000
1.500 1.0354 0.00776 0.00417 -0.2193 0.8945 1.0000
1.750 1.0617 0.00759 0.00402 -0.2187 0.8866 1.0000
2.000 1.0951 0.00723 0.00365 -0.2195 0.8775 1.0000
2.250 1.1213 0.00714 0.00358 -0.2189 0.8677 1.0000
2.500 1.1476 0.00707 0.00352 -0.2183 0.8554 1.0000
2.750 1.1755 0.00695 0.00341 -0.2180 0.8340 1.0000
3.000 1.2065 0.00689 0.00316 -0.2182 0.7822 1.0000
3.250 1.2146 0.00804 0.00344 -0.2135 0.6373 1.0000
3.500 1.2212 0.00919 0.00402 -0.2090 0.5366 1.0000
3.750 1.2318 0.01022 0.00457 -0.2056 0.4477 1.0000
4.000 1.2478 0.01105 0.00507 -0.2034 0.3847 1.0000
4.250 1.2625 0.01212 0.00565 -0.2010 0.2909 1.0000
4.500 1.2805 0.01298 0.00621 -0.1993 0.2348 1.0000
4.750 1.2981 0.01396 0.00679 -0.1976 0.1644 1.0000
5.000 1.3144 0.01515 0.00751 -0.1957 0.0841 1.0000
5.250 1.3304 0.01645 0.00842 -0.1936 0.0256 1.0000
5.500 1.3509 0.01718 0.00918 -0.1920 0.0184 1.0000
5.750 1.3714 0.01784 0.00995 -0.1906 0.0166 1.0000
6.000 1.3908 0.01863 0.01083 -0.1889 0.0152 1.0000
6.250 1.4084 0.01963 0.01193 -0.1868 0.0139 1.0000
6.500 1.4200 0.02133 0.01379 -0.1836 0.0124 1.0000
6.750 1.4354 0.02255 0.01511 -0.1813 0.0119 1.0000
7.000 1.4524 0.02360 0.01629 -0.1792 0.0115 1.0000
7.250 1.4690 0.02487 0.01767 -0.1771 0.0111 1.0000
7.500 1.4865 0.02638 0.01931 -0.1751 0.0106 1.0000
7.750 1.5065 0.02818 0.02125 -0.1736 0.0103 1.0000
8.000 1.5331 0.03060 0.02385 -0.1733 0.0102 1.0000
8.250 1.5666 0.03415 0.02769 -0.1740 0.0105 1.0000
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Polar data table (+)
Polar graphs
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