E591 (e591-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 200,000 Max Cl/Cd: 76.45 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e591-il-200000-n5.txt Download as CSV file: xf-e591-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0573 0.09133 0.08759 -0.0866 0.9400 0.0217
-9.000 -0.0515 0.08656 0.08283 -0.0899 0.9333 0.0215
-8.500 -0.2088 0.04044 0.03601 -0.1302 0.8943 0.0198
-8.250 -0.1847 0.03398 0.02909 -0.1441 0.8842 0.0201
-8.000 -0.1536 0.03040 0.02511 -0.1510 0.8765 0.0205
-7.750 -0.1142 0.02752 0.02186 -0.1573 0.8712 0.0211
-7.500 -0.0826 0.02536 0.01932 -0.1607 0.8618 0.0220
-7.250 -0.0381 0.02349 0.01713 -0.1658 0.8562 0.0229
-7.000 -0.0024 0.02245 0.01600 -0.1683 0.8473 0.0238
-6.750 0.0386 0.02117 0.01451 -0.1718 0.8391 0.0247
-6.500 0.0748 0.02002 0.01314 -0.1741 0.8295 0.0256
-6.250 0.1129 0.01901 0.01196 -0.1767 0.8196 0.0265
-6.000 0.1461 0.01829 0.01118 -0.1782 0.8085 0.0275
-5.500 0.2138 0.01700 0.00965 -0.1811 0.7857 0.0306
-5.250 0.2468 0.01650 0.00907 -0.1825 0.7745 0.0327
-5.000 0.2788 0.01601 0.00846 -0.1835 0.7623 0.0350
-4.750 0.3096 0.01558 0.00795 -0.1843 0.7504 0.0373
-4.500 0.3420 0.01518 0.00743 -0.1853 0.7389 0.0402
-4.250 0.3717 0.01487 0.00704 -0.1858 0.7264 0.0446
-4.000 0.4022 0.01457 0.00665 -0.1864 0.7148 0.0502
-3.750 0.4328 0.01429 0.00630 -0.1871 0.7030 0.0583
-3.500 0.4626 0.01400 0.00599 -0.1876 0.6911 0.0726
-3.250 0.4934 0.01366 0.00568 -0.1884 0.6798 0.1037
-3.000 0.5235 0.01333 0.00549 -0.1891 0.6678 0.1591
-2.750 0.5528 0.01319 0.00541 -0.1894 0.6567 0.2070
-2.500 0.5811 0.01317 0.00537 -0.1895 0.6451 0.2411
-2.250 0.6091 0.01318 0.00537 -0.1894 0.6340 0.2690
-1.750 0.6644 0.01332 0.00542 -0.1890 0.6123 0.3207
-1.500 0.6917 0.01343 0.00542 -0.1887 0.6021 0.3376
-1.250 0.7189 0.01350 0.00547 -0.1884 0.5914 0.3536
-1.000 0.7459 0.01360 0.00550 -0.1881 0.5816 0.3666
-0.750 0.7728 0.01370 0.00551 -0.1878 0.5714 0.3785
-0.500 0.7997 0.01380 0.00556 -0.1874 0.5620 0.3891
-0.250 0.8264 0.01391 0.00560 -0.1871 0.5522 0.4007
0.000 0.8529 0.01403 0.00568 -0.1867 0.5433 0.4114
0.250 0.8795 0.01415 0.00575 -0.1863 0.5339 0.4232
0.500 0.9057 0.01429 0.00584 -0.1859 0.5254 0.4348
0.750 0.9321 0.01441 0.00595 -0.1855 0.5164 0.4471
1.000 0.9580 0.01458 0.00606 -0.1850 0.5083 0.4602
1.250 0.9841 0.01471 0.00620 -0.1846 0.4998 0.4733
1.500 1.0096 0.01488 0.00633 -0.1840 0.4916 0.4877
1.750 1.0354 0.01504 0.00649 -0.1835 0.4840 0.5027
2.000 1.0608 0.01521 0.00666 -0.1830 0.4759 0.5182
2.250 1.0858 0.01541 0.00683 -0.1824 0.4687 0.5349
2.500 1.1113 0.01557 0.00703 -0.1819 0.4610 0.5524
2.750 1.1359 0.01578 0.00723 -0.1812 0.4537 0.5714
3.000 1.1607 0.01597 0.00745 -0.1806 0.4467 0.5918
3.250 1.1851 0.01617 0.00768 -0.1799 0.4393 0.6133
3.750 1.2329 0.01659 0.00818 -0.1783 0.4258 0.6630
4.000 1.2558 0.01681 0.00844 -0.1774 0.4188 0.6909
4.250 1.2779 0.01705 0.00870 -0.1762 0.4127 0.7228
4.500 1.2994 0.01722 0.00897 -0.1749 0.4061 0.7610
4.750 1.3172 0.01740 0.00921 -0.1729 0.3997 0.8091
5.000 1.3252 0.01738 0.00931 -0.1687 0.3946 0.9360
5.250 1.3479 0.01763 0.00957 -0.1678 0.3881 1.0000
5.500 1.3695 0.01800 0.00989 -0.1668 0.3817 1.0000
5.750 1.3908 0.01838 0.01022 -0.1657 0.3760 1.0000
6.000 1.4125 0.01872 0.01056 -0.1647 0.3695 1.0000
6.250 1.4327 0.01912 0.01093 -0.1635 0.3634 1.0000
6.500 1.4527 0.01955 0.01132 -0.1622 0.3578 1.0000
6.750 1.4730 0.01994 0.01173 -0.1611 0.3516 1.0000
7.000 1.4918 0.02040 0.01216 -0.1597 0.3457 1.0000
7.250 1.5105 0.02087 0.01263 -0.1583 0.3404 1.0000
7.500 1.5295 0.02132 0.01311 -0.1570 0.3343 1.0000
7.750 1.5468 0.02185 0.01363 -0.1554 0.3286 1.0000
8.000 1.5639 0.02241 0.01417 -0.1539 0.3234 1.0000
8.250 1.5817 0.02294 0.01475 -0.1525 0.3177 1.0000
8.500 1.5975 0.02355 0.01537 -0.1508 0.3122 1.0000
8.750 1.6126 0.02423 0.01603 -0.1491 0.3072 1.0000
9.000 1.6293 0.02484 0.01671 -0.1477 0.3018 1.0000
9.250 1.6438 0.02556 0.01745 -0.1460 0.2964 1.0000
9.500 1.6565 0.02639 0.01826 -0.1441 0.2916 1.0000
9.750 1.6721 0.02711 0.01906 -0.1427 0.2866 1.0000
10.000 1.6855 0.02794 0.01994 -0.1410 0.2814 1.0000
10.250 1.6969 0.02891 0.02091 -0.1392 0.2767 1.0000
10.500 1.7097 0.02985 0.02190 -0.1376 0.2720 1.0000
10.750 1.7221 0.03082 0.02295 -0.1361 0.2670 1.0000
11.000 1.7323 0.03195 0.02411 -0.1344 0.2623 1.0000
11.250 1.7417 0.03317 0.02535 -0.1327 0.2581 1.0000
11.500 1.7533 0.03430 0.02658 -0.1313 0.2533 1.0000
11.750 1.7624 0.03561 0.02796 -0.1298 0.2486 1.0000
12.000 1.7695 0.03711 0.02947 -0.1281 0.2444 1.0000
12.250 1.7786 0.03852 0.03097 -0.1268 0.2401 1.0000
12.500 1.7869 0.04004 0.03258 -0.1255 0.2355 1.0000
12.750 1.7928 0.04177 0.03436 -0.1241 0.2312 1.0000
13.000 1.7976 0.04366 0.03627 -0.1228 0.2274 1.0000
13.250 1.8054 0.04538 0.03812 -0.1218 0.2230 1.0000
13.500 1.8106 0.04737 0.04020 -0.1207 0.2187 1.0000
13.750 1.8137 0.04959 0.04246 -0.1197 0.2147 1.0000
14.000 1.8177 0.05181 0.04475 -0.1188 0.2110 1.0000
14.250 1.8224 0.05405 0.04712 -0.1181 0.2068 1.0000
14.500 1.8247 0.05657 0.04972 -0.1174 0.2027 1.0000
14.750 1.8256 0.05930 0.05248 -0.1168 0.1991 1.0000
15.000 1.8282 0.06193 0.05523 -0.1163 0.1955 1.0000
15.250 1.8299 0.06474 0.05816 -0.1160 0.1915 1.0000
15.500 1.8297 0.06782 0.06132 -0.1158 0.1877 1.0000
15.750 1.8287 0.07103 0.06456 -0.1156 0.1844 1.0000
16.000 1.8294 0.07417 0.06784 -0.1157 0.1808 1.0000
16.250 1.8285 0.07755 0.07136 -0.1158 0.1770 1.0000
16.500 1.8261 0.08116 0.07504 -0.1161 0.1734 1.0000
16.750 1.8240 0.08474 0.07863 -0.1164 0.1703 1.0000
17.000 1.8223 0.08845 0.08252 -0.1169 0.1668 1.0000
17.250 1.8192 0.09236 0.08656 -0.1176 0.1632 1.0000
17.500 1.8157 0.09633 0.09060 -0.1184 0.1598 1.0000
17.750 1.8137 0.10002 0.09430 -0.1191 0.1568 1.0000
18.000 1.8095 0.10427 0.09875 -0.1202 0.1534 1.0000
18.250 1.8046 0.10861 0.10321 -0.1214 0.1500 1.0000
18.500 1.8011 0.11269 0.10735 -0.1226 0.1468 1.0000
18.750 1.7996 0.11639 0.11107 -0.1237 0.1439 1.0000
19.000 1.7932 0.12110 0.11596 -0.1254 0.1406 1.0000
19.250 1.7879 0.12555 0.12053 -0.1271 0.1372 1.0000
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Polar data table (+)
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