E591 (e591-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E591 (e591-il) Reynolds number: 500,000 Max Cl/Cd: 99.47 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e591-il-500000-n5.txt Download as CSV file: xf-e591-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E591
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3480 0.05459 0.05140 -0.1140 0.9582 0.0126
-11.000 -0.3700 0.04663 0.04325 -0.1216 0.9472 0.0125
-10.750 -0.3825 0.04036 0.03680 -0.1280 0.9365 0.0125
-10.500 -0.3876 0.03445 0.03068 -0.1350 0.9233 0.0126
-10.250 -0.3687 0.02929 0.02528 -0.1450 0.9130 0.0127
-10.000 -0.3269 0.02483 0.02048 -0.1577 0.9073 0.0130
-9.750 -0.2923 0.02265 0.01806 -0.1633 0.8990 0.0131
-9.500 -0.2488 0.02080 0.01601 -0.1694 0.8925 0.0133
-9.250 -0.2062 0.01931 0.01438 -0.1747 0.8845 0.0136
-9.000 -0.1619 0.01824 0.01318 -0.1795 0.8753 0.0139
-8.750 -0.1239 0.01742 0.01225 -0.1827 0.8638 0.0142
-8.500 -0.0873 0.01666 0.01135 -0.1854 0.8518 0.0145
-8.250 -0.0548 0.01602 0.01056 -0.1870 0.8377 0.0149
-8.000 -0.0250 0.01542 0.00982 -0.1880 0.8240 0.0152
-7.750 0.0045 0.01490 0.00916 -0.1888 0.8103 0.0156
-7.500 0.0333 0.01444 0.00855 -0.1894 0.7969 0.0160
-7.250 0.0613 0.01396 0.00796 -0.1898 0.7830 0.0164
-7.000 0.0893 0.01358 0.00749 -0.1902 0.7701 0.0169
-6.750 0.1171 0.01329 0.00710 -0.1903 0.7573 0.0174
-6.500 0.1447 0.01302 0.00674 -0.1904 0.7440 0.0182
-6.250 0.1726 0.01277 0.00637 -0.1905 0.7317 0.0191
-6.000 0.2005 0.01248 0.00599 -0.1906 0.7197 0.0198
-5.750 0.2285 0.01224 0.00568 -0.1907 0.7069 0.0207
-5.500 0.2565 0.01204 0.00538 -0.1908 0.6951 0.0217
-5.250 0.2844 0.01184 0.00508 -0.1908 0.6831 0.0228
-5.000 0.3129 0.01164 0.00482 -0.1909 0.6714 0.0242
-4.750 0.3406 0.01151 0.00459 -0.1909 0.6596 0.0258
-4.500 0.3690 0.01135 0.00437 -0.1909 0.6478 0.0277
-4.250 0.3971 0.01125 0.00418 -0.1909 0.6368 0.0303
-4.000 0.4251 0.01113 0.00400 -0.1909 0.6250 0.0333
-3.750 0.4536 0.01102 0.00384 -0.1910 0.6142 0.0367
-3.500 0.4814 0.01095 0.00369 -0.1909 0.6033 0.0414
-3.250 0.5102 0.01083 0.00356 -0.1910 0.5924 0.0498
-3.000 0.5386 0.01072 0.00345 -0.1912 0.5822 0.0677
-2.750 0.5679 0.01055 0.00334 -0.1915 0.5715 0.0977
-2.500 0.5971 0.01038 0.00326 -0.1919 0.5616 0.1429
-2.250 0.6260 0.01028 0.00322 -0.1922 0.5513 0.1839
-2.000 0.6542 0.01026 0.00322 -0.1922 0.5420 0.2150
-1.750 0.6821 0.01028 0.00323 -0.1921 0.5320 0.2377
-1.500 0.7099 0.01031 0.00327 -0.1920 0.5233 0.2606
-1.250 0.7378 0.01035 0.00332 -0.1919 0.5140 0.2847
-1.000 0.7650 0.01043 0.00337 -0.1917 0.5054 0.3027
-0.750 0.7926 0.01049 0.00342 -0.1915 0.4966 0.3198
-0.500 0.8194 0.01061 0.00349 -0.1912 0.4884 0.3343
-0.250 0.8471 0.01067 0.00354 -0.1910 0.4803 0.3441
0.000 0.8737 0.01079 0.00361 -0.1906 0.4719 0.3538
0.250 0.9009 0.01089 0.00368 -0.1904 0.4647 0.3631
0.500 0.9277 0.01100 0.00377 -0.1901 0.4568 0.3732
0.750 0.9540 0.01114 0.00386 -0.1896 0.4494 0.3820
1.000 0.9811 0.01123 0.00395 -0.1894 0.4422 0.3933
1.250 1.0071 0.01138 0.00406 -0.1889 0.4349 0.4031
1.500 1.0337 0.01150 0.00418 -0.1886 0.4284 0.4144
1.750 1.0600 0.01163 0.00430 -0.1882 0.4211 0.4258
2.000 1.0854 0.01180 0.00444 -0.1877 0.4145 0.4379
2.250 1.1119 0.01191 0.00457 -0.1874 0.4082 0.4504
2.500 1.1375 0.01207 0.00472 -0.1869 0.4013 0.4640
2.750 1.1625 0.01225 0.00489 -0.1863 0.3950 0.4776
3.000 1.1884 0.01238 0.00504 -0.1858 0.3890 0.4925
3.250 1.2128 0.01255 0.00522 -0.1851 0.3823 0.5082
3.500 1.2367 0.01274 0.00541 -0.1843 0.3762 0.5241
3.750 1.2616 0.01288 0.00559 -0.1837 0.3705 0.5419
4.000 1.2851 0.01307 0.00579 -0.1829 0.3640 0.5604
4.250 1.3083 0.01327 0.00601 -0.1820 0.3581 0.5795
4.500 1.3325 0.01345 0.00623 -0.1813 0.3522 0.5999
4.750 1.3552 0.01367 0.00648 -0.1803 0.3459 0.6234
5.250 1.4015 0.01409 0.00700 -0.1786 0.3343 0.6734
5.500 1.4234 0.01434 0.00728 -0.1775 0.3283 0.7041
5.750 1.4451 0.01456 0.00758 -0.1764 0.3229 0.7404
6.250 1.4844 0.01496 0.00819 -0.1733 0.3114 0.8463
6.500 1.4967 0.01506 0.00839 -0.1702 0.3068 1.0000
6.750 1.5187 0.01536 0.00869 -0.1693 0.3013 1.0000
7.000 1.5389 0.01574 0.00905 -0.1680 0.2955 1.0000
7.250 1.5583 0.01614 0.00943 -0.1667 0.2905 1.0000
7.500 1.5793 0.01648 0.00977 -0.1656 0.2855 1.0000
7.750 1.5985 0.01690 0.01018 -0.1643 0.2798 1.0000
8.000 1.6160 0.01740 0.01065 -0.1627 0.2749 1.0000
8.250 1.6361 0.01778 0.01106 -0.1615 0.2704 1.0000
8.500 1.6545 0.01825 0.01153 -0.1602 0.2651 1.0000
8.750 1.6705 0.01883 0.01209 -0.1585 0.2600 1.0000
9.000 1.6887 0.01931 0.01260 -0.1571 0.2558 1.0000
9.250 1.7061 0.01984 0.01315 -0.1557 0.2510 1.0000
9.500 1.7214 0.02049 0.01379 -0.1540 0.2459 1.0000
9.750 1.7365 0.02116 0.01447 -0.1523 0.2416 1.0000
10.000 1.7531 0.02176 0.01510 -0.1509 0.2373 1.0000
10.250 1.7675 0.02250 0.01585 -0.1493 0.2326 1.0000
10.500 1.7796 0.02339 0.01674 -0.1474 0.2279 1.0000
10.750 1.7948 0.02411 0.01751 -0.1459 0.2240 1.0000
11.000 1.8086 0.02494 0.01838 -0.1444 0.2195 1.0000
11.250 1.8195 0.02597 0.01942 -0.1426 0.2151 1.0000
11.500 1.8311 0.02700 0.02047 -0.1409 0.2111 1.0000
11.750 1.8438 0.02797 0.02149 -0.1395 0.2070 1.0000
12.000 1.8542 0.02914 0.02270 -0.1379 0.2027 1.0000
12.250 1.8618 0.03054 0.02412 -0.1361 0.1985 1.0000
12.500 1.8731 0.03172 0.02535 -0.1348 0.1950 1.0000
12.750 1.8829 0.03305 0.02673 -0.1334 0.1911 1.0000
13.000 1.8901 0.03463 0.02835 -0.1319 0.1871 1.0000
13.250 1.8958 0.03640 0.03015 -0.1304 0.1834 1.0000
13.500 1.9050 0.03791 0.03173 -0.1293 0.1800 1.0000
13.750 1.9120 0.03967 0.03355 -0.1281 0.1762 1.0000
14.000 1.9159 0.04177 0.03569 -0.1269 0.1725 1.0000
14.250 1.9198 0.04394 0.03791 -0.1258 0.1691 1.0000
14.500 1.9262 0.04592 0.03997 -0.1250 0.1658 1.0000
14.750 1.9300 0.04823 0.04234 -0.1241 0.1623 1.0000
15.000 1.9306 0.05096 0.04512 -0.1233 0.1588 1.0000
15.250 1.9325 0.05360 0.04782 -0.1226 0.1557 1.0000
15.500 1.9360 0.05614 0.05045 -0.1221 0.1527 1.0000
15.750 1.9367 0.05907 0.05345 -0.1217 0.1493 1.0000
16.000 1.9339 0.06252 0.05695 -0.1214 0.1460 1.0000
16.250 1.9332 0.06576 0.06027 -0.1212 0.1431 1.0000
16.500 1.9342 0.06884 0.06344 -0.1211 0.1402 1.0000
16.750 1.9316 0.07247 0.06714 -0.1212 0.1369 1.0000
17.000 1.9257 0.07663 0.07137 -0.1215 0.1339 1.0000
17.250 1.9221 0.08053 0.07535 -0.1218 0.1312 1.0000
17.500 1.9211 0.08409 0.07901 -0.1222 0.1283 1.0000
17.750 1.9162 0.08829 0.08329 -0.1228 0.1252 1.0000
18.000 1.9077 0.09309 0.08816 -0.1237 0.1223 1.0000
18.250 1.9025 0.09743 0.09258 -0.1245 0.1197 1.0000
18.500 1.9003 0.10133 0.09657 -0.1253 0.1169 1.0000
18.750 1.8937 0.10594 0.10126 -0.1265 0.1140 1.0000
19.000 1.8840 0.11108 0.10647 -0.1279 0.1111 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E591 (e591-il)