EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 1,000,000 Max Cl/Cd: 160.82 at α=0° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e58-il-1000000-n5.txt Download as CSV file: xf-e58-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0099 0.09205 0.09016 -0.1204 0.9694 0.0043
-11.000 0.0197 0.08884 0.08696 -0.1221 0.9691 0.0053
-10.500 -0.0750 0.10451 0.10254 -0.1134 0.9706 0.0044
-10.250 -0.0626 0.10128 0.09931 -0.1159 0.9701 0.0043
-10.000 -0.0493 0.09830 0.09633 -0.1184 0.9696 0.0047
-9.750 -0.0354 0.09516 0.09319 -0.1212 0.9692 0.0049
-9.500 -0.0304 0.09281 0.09085 -0.1212 0.9663 0.0050
-9.250 -0.0196 0.08976 0.08780 -0.1231 0.9641 0.0056
-8.250 0.0374 0.07589 0.07392 -0.1357 0.9594 0.0035
-8.000 0.0551 0.07261 0.07064 -0.1398 0.9583 0.0033
-7.750 0.0670 0.06952 0.06756 -0.1423 0.9557 0.0033
-7.500 0.0709 0.06698 0.06503 -0.1425 0.9510 0.0033
-7.250 0.0826 0.06428 0.06232 -0.1447 0.9480 0.0032
-6.750 0.1096 0.05688 0.05492 -0.1525 0.9413 0.0034
-6.250 0.2313 0.01266 0.00921 -0.2261 0.9274 0.0037
-6.000 0.2651 0.01106 0.00729 -0.2287 0.9262 0.0040
-5.750 0.2948 0.01052 0.00664 -0.2296 0.9250 0.0044
-5.500 0.3255 0.00989 0.00586 -0.2306 0.9239 0.0048
-5.250 0.3570 0.00917 0.00494 -0.2318 0.9228 0.0053
-5.000 0.3880 0.00866 0.00428 -0.2328 0.9214 0.0057
-4.750 0.4199 0.00806 0.00352 -0.2339 0.9198 0.0066
-4.500 0.4511 0.00773 0.00312 -0.2348 0.9182 0.0077
-4.250 0.4808 0.00750 0.00281 -0.2353 0.9162 0.0090
-4.000 0.5086 0.00723 0.00253 -0.2354 0.9136 0.0122
-3.750 0.5364 0.00711 0.00242 -0.2354 0.9108 0.0153
-3.500 0.5649 0.00699 0.00230 -0.2356 0.9076 0.0196
-3.250 0.5946 0.00691 0.00219 -0.2360 0.9043 0.0241
-3.000 0.6214 0.00688 0.00214 -0.2357 0.8997 0.0264
-2.750 0.6482 0.00686 0.00211 -0.2355 0.8950 0.0274
-2.500 0.6769 0.00682 0.00204 -0.2357 0.8912 0.0278
-2.250 0.7067 0.00658 0.00173 -0.2362 0.8883 0.0289
-2.000 0.7346 0.00645 0.00157 -0.2363 0.8846 0.0293
-1.750 0.7631 0.00632 0.00141 -0.2365 0.8805 0.0301
-1.500 0.7924 0.00623 0.00127 -0.2369 0.8764 0.0302
-1.250 0.8197 0.00617 0.00120 -0.2368 0.8715 0.0302
-1.000 0.8477 0.00611 0.00110 -0.2368 0.8653 0.0303
-0.750 0.8751 0.00607 0.00102 -0.2367 0.8562 0.0306
-0.500 0.9025 0.00605 0.00095 -0.2366 0.8454 0.0318
-0.250 0.9296 0.00605 0.00092 -0.2364 0.8330 0.0358
0.000 0.9569 0.00595 0.00094 -0.2364 0.8141 0.1164
0.250 0.9795 0.00614 0.00100 -0.2352 0.7768 0.1345
0.500 0.9943 0.00668 0.00121 -0.2323 0.7052 0.1458
0.750 1.0097 0.00727 0.00150 -0.2296 0.6429 0.1534
1.000 1.0304 0.00763 0.00171 -0.2282 0.6080 0.1617
1.250 1.0504 0.00805 0.00195 -0.2266 0.5621 0.1717
1.500 1.0661 0.00878 0.00230 -0.2242 0.4759 0.1839
1.750 1.0852 0.00937 0.00264 -0.2226 0.4151 0.2043
2.000 1.1079 0.00975 0.00294 -0.2218 0.3707 0.2725
2.250 1.1343 0.00990 0.00330 -0.2221 0.3290 0.4834
2.500 1.1605 0.01007 0.00379 -0.2222 0.2826 0.7488
2.750 1.1820 0.01022 0.00409 -0.2210 0.2600 0.8837
3.000 1.1985 0.01058 0.00435 -0.2187 0.2154 1.0000
3.250 1.2184 0.01131 0.00476 -0.2173 0.1581 1.0000
3.500 1.2415 0.01169 0.00507 -0.2165 0.1381 1.0000
3.750 1.2610 0.01250 0.00554 -0.2151 0.0753 1.0000
4.000 1.2831 0.01301 0.00594 -0.2140 0.0517 1.0000
4.250 1.3036 0.01371 0.00644 -0.2127 0.0162 1.0000
4.500 1.3267 0.01409 0.00682 -0.2119 0.0096 1.0000
4.750 1.3497 0.01446 0.00723 -0.2110 0.0076 1.0000
5.000 1.3719 0.01490 0.00770 -0.2099 0.0060 1.0000
5.250 1.3939 0.01529 0.00812 -0.2088 0.0052 1.0000
5.500 1.4153 0.01573 0.00858 -0.2076 0.0045 1.0000
5.750 1.4357 0.01629 0.00918 -0.2062 0.0038 1.0000
6.000 1.4566 0.01675 0.00971 -0.2049 0.0034 1.0000
6.250 1.4768 0.01728 0.01028 -0.2035 0.0031 1.0000
6.500 1.4967 0.01784 0.01089 -0.2021 0.0028 1.0000
6.750 1.5160 0.01844 0.01153 -0.2006 0.0026 1.0000
7.000 1.5326 0.01940 0.01258 -0.1985 0.0023 1.0000
7.250 1.5499 0.02019 0.01344 -0.1966 0.0022 1.0000
7.500 1.5667 0.02102 0.01436 -0.1945 0.0021 1.0000
7.750 1.5823 0.02195 0.01540 -0.1923 0.0020 1.0000
8.000 1.5975 0.02292 0.01646 -0.1901 0.0018 1.0000
8.250 1.6129 0.02384 0.01747 -0.1880 0.0017 1.0000
8.500 1.6286 0.02470 0.01844 -0.1860 0.0016 1.0000
8.750 1.6443 0.02553 0.01934 -0.1841 0.0015 1.0000
9.000 1.6583 0.02658 0.02048 -0.1819 0.0014 1.0000
9.250 1.6711 0.02774 0.02174 -0.1795 0.0013 1.0000
9.500 1.6813 0.02928 0.02341 -0.1767 0.0013 1.0000
9.750 1.6888 0.03122 0.02552 -0.1736 0.0012 1.0000
10.000 1.6968 0.03316 0.02764 -0.1706 0.0012 1.0000
10.250 1.7053 0.03504 0.02971 -0.1678 0.0011 1.0000
10.500 1.7131 0.03696 0.03181 -0.1649 0.0011 1.0000
10.750 1.7170 0.03956 0.03466 -0.1616 0.0011 1.0000
11.000 1.7210 0.04195 0.03725 -0.1585 0.0011 1.0000
11.250 1.7201 0.04519 0.04078 -0.1549 0.0010 1.0000
11.500 1.7126 0.04940 0.04532 -0.1507 0.0010 1.0000
11.750 1.6992 0.05448 0.05076 -0.1462 0.0009 1.0000
12.000 1.6826 0.05981 0.05642 -0.1421 0.0008 1.0000
12.250 1.6507 0.06767 0.06470 -0.1377 0.0008 1.0000
12.500 1.6189 0.07544 0.07280 -0.1348 0.0008 1.0000
12.750 1.5959 0.08205 0.07966 -0.1335 0.0008 1.0000
13.000 1.5744 0.08884 0.08667 -0.1335 0.0007 1.0000
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Polar data table (+)
Polar graphs
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