EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 500,000 Max Cl/Cd: 166.55 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e58-il-500000-n5.txt Download as CSV file: xf-e58-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 0.0039 0.07156 0.06900 -0.1196 0.9450 0.0057
-6.500 0.0060 0.06727 0.06474 -0.1184 0.9348 0.0056
-6.250 0.0260 0.06339 0.06086 -0.1237 0.9332 0.0056
-6.000 0.0513 0.05925 0.05671 -0.1305 0.9320 0.0056
-5.750 0.0698 0.05553 0.05299 -0.1355 0.9289 0.0056
-5.500 0.0722 0.05295 0.05043 -0.1360 0.9219 0.0062
-5.250 0.1031 0.04965 0.04710 -0.1427 0.9205 0.0066
-4.750 0.3255 0.01498 0.01053 -0.2132 0.9227 0.0075
-4.500 0.3656 0.01329 0.00839 -0.2167 0.9226 0.0085
-4.250 0.4022 0.01218 0.00699 -0.2191 0.9223 0.0103
-4.000 0.4343 0.01184 0.00657 -0.2202 0.9215 0.0123
-3.750 0.4678 0.01138 0.00600 -0.2215 0.9208 0.0147
-3.500 0.5014 0.01101 0.00556 -0.2229 0.9199 0.0184
-3.250 0.5354 0.01069 0.00518 -0.2242 0.9190 0.0233
-3.000 0.5687 0.01053 0.00494 -0.2254 0.9181 0.0271
-2.750 0.6043 0.01006 0.00440 -0.2272 0.9172 0.0300
-2.500 0.6232 0.00996 0.00429 -0.2254 0.9121 0.0328
-2.250 0.6536 0.00966 0.00393 -0.2260 0.9090 0.0342
-2.000 0.6874 0.00933 0.00354 -0.2272 0.9065 0.0352
-1.750 0.7228 0.00900 0.00315 -0.2288 0.9042 0.0365
-1.500 0.7481 0.00888 0.00299 -0.2282 0.8997 0.0366
-1.250 0.7753 0.00875 0.00282 -0.2280 0.8952 0.0369
-1.000 0.8069 0.00856 0.00260 -0.2288 0.8919 0.0374
-0.750 0.8397 0.00839 0.00240 -0.2298 0.8895 0.0392
-0.500 0.8629 0.00828 0.00244 -0.2289 0.8836 0.0829
-0.250 0.8931 0.00811 0.00239 -0.2295 0.8789 0.1362
0.000 0.9212 0.00801 0.00235 -0.2295 0.8726 0.1552
0.250 0.9492 0.00794 0.00231 -0.2295 0.8659 0.1667
0.500 0.9773 0.00788 0.00230 -0.2296 0.8596 0.1798
0.750 1.0059 0.00780 0.00228 -0.2298 0.8515 0.2004
1.000 1.0339 0.00771 0.00232 -0.2299 0.8423 0.2508
1.250 1.0667 0.00734 0.00246 -0.2313 0.8321 0.4903
1.500 1.0972 0.00696 0.00264 -0.2320 0.8151 0.7540
1.750 1.1159 0.00670 0.00251 -0.2295 0.7755 0.9674
2.000 1.1297 0.00748 0.00269 -0.2262 0.6728 1.0000
2.250 1.1397 0.00842 0.00315 -0.2224 0.5958 1.0000
2.500 1.1533 0.00920 0.00357 -0.2195 0.5236 1.0000
2.750 1.1681 0.00999 0.00401 -0.2169 0.4553 1.0000
3.000 1.1881 0.01051 0.00436 -0.2154 0.4202 1.0000
3.250 1.2092 0.01097 0.00469 -0.2142 0.3902 1.0000
3.500 1.2255 0.01186 0.00517 -0.2121 0.3097 1.0000
3.750 1.2421 0.01277 0.00573 -0.2102 0.2473 1.0000
4.000 1.2584 0.01379 0.00631 -0.2082 0.1672 1.0000
4.250 1.2785 0.01441 0.00679 -0.2069 0.1368 1.0000
4.500 1.2950 0.01547 0.00747 -0.2050 0.0679 1.0000
4.750 1.3122 0.01648 0.00819 -0.2031 0.0177 1.0000
5.000 1.3329 0.01706 0.00881 -0.2017 0.0115 1.0000
5.250 1.3539 0.01758 0.00942 -0.2004 0.0090 1.0000
5.500 1.3744 0.01814 0.01005 -0.1990 0.0076 1.0000
5.750 1.3937 0.01885 0.01085 -0.1974 0.0065 1.0000
6.000 1.4119 0.01972 0.01183 -0.1956 0.0059 1.0000
6.250 1.4308 0.02045 0.01265 -0.1939 0.0054 1.0000
6.500 1.4492 0.02117 0.01346 -0.1922 0.0047 1.0000
6.750 1.4669 0.02196 0.01429 -0.1905 0.0042 1.0000
7.000 1.4802 0.02329 0.01572 -0.1879 0.0039 1.0000
7.250 1.4948 0.02444 0.01698 -0.1856 0.0037 1.0000
7.500 1.5089 0.02567 0.01834 -0.1831 0.0035 1.0000
7.750 1.5223 0.02706 0.01986 -0.1806 0.0033 1.0000
8.000 1.5352 0.02863 0.02157 -0.1781 0.0031 1.0000
8.250 1.5486 0.03030 0.02340 -0.1756 0.0030 1.0000
8.500 1.5627 0.03216 0.02541 -0.1733 0.0029 1.0000
8.750 1.5772 0.03400 0.02742 -0.1712 0.0027 1.0000
9.000 1.5909 0.03557 0.02918 -0.1691 0.0026 1.0000
9.250 1.6023 0.03693 0.03064 -0.1670 0.0024 1.0000
9.500 1.6119 0.03993 0.03386 -0.1645 0.0023 1.0000
9.750 1.6224 0.04170 0.03592 -0.1618 0.0021 1.0000
10.000 1.6295 0.04476 0.03931 -0.1588 0.0020 1.0000
10.250 1.6318 0.04841 0.04332 -0.1552 0.0020 1.0000
10.500 1.6280 0.05270 0.04801 -0.1511 0.0019 1.0000
10.750 1.6194 0.05702 0.05268 -0.1469 0.0019 1.0000
11.000 1.6084 0.06137 0.05735 -0.1429 0.0018 1.0000
11.250 1.5920 0.06646 0.06277 -0.1390 0.0018 1.0000
11.500 1.5741 0.07171 0.06831 -0.1357 0.0018 1.0000
11.750 1.5542 0.07737 0.07426 -0.1332 0.0017 1.0000
12.000 1.5347 0.08315 0.08028 -0.1317 0.0017 1.0000
12.250 1.5135 0.08955 0.08691 -0.1313 0.0017 1.0000
12.500 1.4935 0.09614 0.09371 -0.1321 0.0018 1.0000
12.750 1.4704 0.10419 0.10199 -0.1344 0.0017 1.0000
13.000 1.4502 0.11254 0.11053 -0.1382 0.0017 1.0000
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Polar data table (+)
Polar graphs
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