EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 200,000 Max Cl/Cd: 106.57 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e58-il-200000-n5.txt Download as CSV file: xf-e58-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1751 0.09660 0.09301 -0.0698 0.9515 0.0129
-7.000 -0.1698 0.09412 0.09054 -0.0694 0.9488 0.0134
-6.750 -0.1623 0.09166 0.08809 -0.0702 0.9464 0.0139
-6.500 -0.1517 0.08904 0.08548 -0.0720 0.9444 0.0145
-6.250 -0.1569 0.08757 0.08405 -0.0697 0.9391 0.0148
-6.000 -0.1499 0.08508 0.08158 -0.0707 0.9353 0.0154
-5.750 -0.1340 0.08187 0.07837 -0.0741 0.9327 0.0164
-5.500 -0.1135 0.07831 0.07481 -0.0790 0.9309 0.0176
-5.250 -0.1035 0.07673 0.07325 -0.0833 0.9234 0.0205
-5.000 -0.0789 0.07313 0.06964 -0.0891 0.9208 0.0207
-4.000 0.0104 0.05744 0.05389 -0.1071 0.9092 0.0252
-3.750 0.0952 0.05108 0.04728 -0.1285 0.9083 0.0329
-3.250 0.2433 0.03349 0.02893 -0.1611 0.9097 0.0215
-3.000 0.3206 0.02735 0.02203 -0.1759 0.9123 0.0234
-2.750 0.3572 0.02643 0.02094 -0.1788 0.9100 0.0295
-2.500 0.4140 0.02332 0.01712 -0.1860 0.9108 0.0269
-2.250 0.4587 0.02159 0.01485 -0.1897 0.9103 0.0250
-2.000 0.4965 0.02057 0.01351 -0.1919 0.9092 0.0238
-1.750 0.5319 0.01988 0.01262 -0.1935 0.9082 0.0230
-1.500 0.5667 0.01933 0.01197 -0.1951 0.9070 0.0225
-1.250 0.6023 0.01885 0.01139 -0.1968 0.9060 0.0222
-1.000 0.6399 0.01834 0.01081 -0.1988 0.9049 0.0222
-0.750 0.6646 0.01818 0.01058 -0.1983 0.8999 0.0223
-0.500 0.6971 0.01783 0.01012 -0.1992 0.8962 0.0231
-0.250 0.7337 0.01742 0.00959 -0.2008 0.8938 0.0245
0.250 0.7989 0.01660 0.00914 -0.2027 0.8850 0.1663
0.500 0.8359 0.01605 0.00882 -0.2045 0.8812 0.2301
0.750 0.8805 0.01491 0.00869 -0.2082 0.8793 0.6068
1.000 0.8931 0.01441 0.00868 -0.2045 0.8712 0.8751
1.250 0.9249 0.01394 0.00819 -0.2048 0.8670 1.0000
1.500 0.9480 0.01397 0.00821 -0.2037 0.8593 1.0000
1.750 0.9790 0.01374 0.00797 -0.2041 0.8547 1.0000
2.000 1.0023 0.01378 0.00806 -0.2031 0.8464 1.0000
2.250 1.0341 0.01349 0.00778 -0.2036 0.8404 1.0000
2.500 1.0562 0.01355 0.00787 -0.2023 0.8293 1.0000
2.750 1.0817 0.01348 0.00783 -0.2016 0.8173 1.0000
3.000 1.1100 0.01329 0.00768 -0.2014 0.8035 1.0000
3.250 1.1461 0.01277 0.00722 -0.2024 0.7787 1.0000
3.500 1.2277 0.01152 0.00561 -0.2122 0.6952 1.0000
3.750 1.2572 0.01207 0.00568 -0.2122 0.6221 1.0000
4.000 1.2745 0.01281 0.00614 -0.2099 0.5654 1.0000
4.250 1.2881 0.01363 0.00668 -0.2071 0.5020 1.0000
4.500 1.2867 0.01522 0.00755 -0.2014 0.3976 1.0000
4.750 1.2878 0.01697 0.00850 -0.1967 0.2737 1.0000
5.000 1.3030 0.01796 0.00922 -0.1945 0.2152 1.0000
5.250 1.3112 0.01983 0.01045 -0.1914 0.0990 1.0000
5.500 1.3197 0.02189 0.01182 -0.1884 0.0133 1.0000
5.750 1.3381 0.02278 0.01277 -0.1866 0.0085 1.0000
6.000 1.3572 0.02357 0.01369 -0.1849 0.0077 1.0000
6.250 1.3757 0.02442 0.01470 -0.1832 0.0073 1.0000
6.500 1.3935 0.02537 0.01582 -0.1814 0.0070 1.0000
6.750 1.4101 0.02644 0.01706 -0.1793 0.0068 1.0000
7.000 1.4253 0.02763 0.01843 -0.1771 0.0066 1.0000
7.250 1.4389 0.02899 0.01996 -0.1747 0.0065 1.0000
7.500 1.4512 0.03050 0.02162 -0.1721 0.0064 1.0000
7.750 1.4628 0.03218 0.02345 -0.1694 0.0064 1.0000
8.000 1.4746 0.03399 0.02542 -0.1668 0.0063 1.0000
8.250 1.4875 0.03596 0.02754 -0.1644 0.0063 1.0000
8.500 1.5019 0.03795 0.02971 -0.1623 0.0059 1.0000
8.750 1.5157 0.03982 0.03194 -0.1603 0.0052 1.0000
9.000 1.5268 0.04192 0.03420 -0.1582 0.0045 1.0000
9.250 1.5393 0.04480 0.03733 -0.1561 0.0042 1.0000
9.500 1.5510 0.04862 0.04150 -0.1539 0.0039 1.0000
9.750 1.5581 0.05205 0.04528 -0.1512 0.0039 1.0000
10.000 1.5589 0.05602 0.04965 -0.1479 0.0038 1.0000
10.250 1.5549 0.05999 0.05400 -0.1443 0.0038 1.0000
10.500 1.5473 0.06405 0.05842 -0.1407 0.0038 1.0000
10.750 1.5367 0.06831 0.06301 -0.1372 0.0038 1.0000
11.000 1.5242 0.07267 0.06770 -0.1341 0.0038 1.0000
11.250 1.5126 0.07690 0.07220 -0.1317 0.0038 1.0000
11.500 1.4954 0.08212 0.07774 -0.1297 0.0038 1.0000
11.750 1.4820 0.08690 0.08276 -0.1286 0.0038 1.0000
12.000 1.4628 0.09292 0.08906 -0.1283 0.0038 1.0000
12.250 1.4507 0.09804 0.09440 -0.1288 0.0039 1.0000
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Polar data table (+)
Polar graphs
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