E591 (e591-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E591 (e591-il) Reynolds number: 100,000 Max Cl/Cd: 52.16 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e591-il-100000.txt Download as CSV file: xf-e591-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1178 0.10555 0.10135 -0.0656 0.9399 0.1240
-7.000 -0.0733 0.10130 0.09706 -0.0669 0.9373 0.1307
-6.750 -0.1055 0.10083 0.09667 -0.0738 0.9201 0.1365
-6.500 -0.0609 0.09520 0.09102 -0.0728 0.9160 0.1397
-6.250 -0.0347 0.09181 0.08761 -0.0755 0.9095 0.1460
-6.000 -0.0636 0.08981 0.08569 -0.0820 0.8924 0.1524
-5.750 -0.0158 0.08547 0.08130 -0.0810 0.8913 0.1561
-5.500 -0.0238 0.08331 0.07918 -0.0869 0.8753 0.1666
-5.250 -0.0353 0.04841 0.04323 -0.1325 0.8597 0.0798
-5.000 0.0282 0.04001 0.03388 -0.1463 0.8571 0.0744
-4.750 0.0921 0.03544 0.02849 -0.1554 0.8550 0.0765
-4.500 0.1248 0.03354 0.02595 -0.1574 0.8435 0.0784
-4.250 0.1749 0.03088 0.02323 -0.1614 0.8400 0.0816
-4.000 0.2315 0.02863 0.02067 -0.1660 0.8377 0.0888
-3.750 0.2610 0.02769 0.01975 -0.1663 0.8272 0.0956
-3.500 0.3121 0.02597 0.01801 -0.1698 0.8225 0.1088
-3.250 0.3718 0.02410 0.01629 -0.1751 0.8196 0.1352
-3.000 0.4160 0.02275 0.01544 -0.1784 0.8109 0.2129
-2.750 0.4636 0.02253 0.01535 -0.1814 0.8031 0.3175
-2.500 0.5152 0.02232 0.01514 -0.1844 0.7983 0.3643
-2.250 0.5361 0.02271 0.01558 -0.1825 0.7847 0.3915
-2.000 0.5858 0.02234 0.01508 -0.1854 0.7787 0.4247
-1.750 0.6072 0.02252 0.01522 -0.1838 0.7651 0.4442
-1.500 0.6440 0.02231 0.01493 -0.1847 0.7558 0.4656
-1.250 0.6745 0.02221 0.01475 -0.1846 0.7444 0.4839
-1.000 0.7040 0.02213 0.01464 -0.1844 0.7337 0.4993
-0.750 0.7383 0.02191 0.01430 -0.1851 0.7234 0.5160
-0.500 0.7653 0.02194 0.01427 -0.1847 0.7117 0.5315
-0.250 0.8023 0.02173 0.01389 -0.1859 0.7025 0.5496
0.000 0.8251 0.02189 0.01403 -0.1848 0.6903 0.5652
0.250 0.8620 0.02171 0.01371 -0.1858 0.6818 0.5831
0.500 0.8812 0.02193 0.01398 -0.1841 0.6695 0.5982
0.750 0.9159 0.02185 0.01377 -0.1849 0.6609 0.6177
1.000 0.9367 0.02206 0.01402 -0.1835 0.6492 0.6355
1.250 0.9687 0.02207 0.01392 -0.1838 0.6407 0.6569
1.500 0.9896 0.02228 0.01419 -0.1824 0.6297 0.6776
1.750 1.0210 0.02232 0.01412 -0.1826 0.6214 0.7030
2.000 1.0403 0.02256 0.01445 -0.1809 0.6107 0.7275
2.250 1.0706 0.02254 0.01431 -0.1807 0.6033 0.7572
2.500 1.0841 0.02283 0.01475 -0.1779 0.5927 0.7875
2.750 1.1086 0.02273 0.01458 -0.1765 0.5855 0.8281
3.000 1.1140 0.02285 0.01489 -0.1720 0.5765 0.8810
3.250 1.1445 0.02273 0.01467 -0.1726 0.5680 1.0000
3.500 1.1782 0.02331 0.01513 -0.1744 0.5584 1.0000
3.750 1.2115 0.02367 0.01532 -0.1757 0.5497 1.0000
4.000 1.2402 0.02419 0.01573 -0.1761 0.5412 1.0000
4.250 1.2663 0.02464 0.01611 -0.1760 0.5322 1.0000
4.500 1.2990 0.02504 0.01632 -0.1768 0.5248 1.0000
4.750 1.3180 0.02567 0.01702 -0.1755 0.5155 1.0000
5.000 1.3530 0.02594 0.01707 -0.1767 0.5085 1.0000
5.250 1.3690 0.02672 0.01795 -0.1749 0.4996 1.0000
5.500 1.3978 0.02709 0.01822 -0.1750 0.4920 1.0000
5.750 1.4217 0.02772 0.01883 -0.1745 0.4845 1.0000
6.000 1.4421 0.02833 0.01946 -0.1733 0.4763 1.0000
6.250 1.4793 0.02861 0.01952 -0.1748 0.4699 1.0000
6.500 1.4881 0.02957 0.02068 -0.1719 0.4614 1.0000
6.750 1.5164 0.02995 0.02097 -0.1720 0.4543 1.0000
7.000 1.5384 0.03068 0.02171 -0.1712 0.4473 1.0000
7.250 1.5547 0.03143 0.02255 -0.1695 0.4396 1.0000
7.500 1.5909 0.03169 0.02261 -0.1708 0.4333 1.0000
7.750 1.5978 0.03281 0.02395 -0.1677 0.4258 1.0000
8.000 1.6199 0.03337 0.02451 -0.1669 0.4188 1.0000
8.250 1.6515 0.03386 0.02488 -0.1675 0.4127 1.0000
8.500 1.6548 0.03504 0.02629 -0.1640 0.4053 1.0000
8.750 1.6826 0.03545 0.02663 -0.1640 0.3989 1.0000
9.000 1.7018 0.03634 0.02755 -0.1629 0.3927 1.0000
9.250 1.7072 0.03747 0.02885 -0.1597 0.3858 1.0000
9.500 1.7408 0.03771 0.02898 -0.1606 0.3798 1.0000
9.750 1.7478 0.03899 0.03041 -0.1578 0.3737 1.0000
10.000 1.7519 0.04017 0.03174 -0.1545 0.3674 1.0000
10.250 1.7910 0.04026 0.03167 -0.1562 0.3615 1.0000
10.500 1.7871 0.04188 0.03350 -0.1519 0.3559 1.0000
10.750 1.7820 0.04331 0.03511 -0.1475 0.3502 1.0000
11.000 1.8237 0.04330 0.03495 -0.1495 0.3442 1.0000
11.250 1.8181 0.04501 0.03683 -0.1452 0.3392 1.0000
11.500 1.7990 0.04721 0.03928 -0.1395 0.3340 1.0000
11.750 1.8257 0.04754 0.03957 -0.1394 0.3285 1.0000
12.000 1.8464 0.04850 0.04053 -0.1388 0.3232 1.0000
12.250 1.8058 0.05211 0.04448 -0.1317 0.3188 1.0000
12.500 1.8052 0.05392 0.04640 -0.1291 0.3137 1.0000
12.750 1.8762 0.05222 0.04444 -0.1333 0.3076 1.0000
13.000 1.8081 0.05798 0.05065 -0.1250 0.3042 1.0000
13.250 1.7291 0.06657 0.05963 -0.1193 0.2998 1.0000
13.500 1.7899 0.06361 0.05654 -0.1203 0.2946 1.0000
13.750 1.8182 0.06396 0.05688 -0.1202 0.2898 1.0000
14.000 1.1759 0.17210 0.16595 -0.1536 0.2563 1.0000
14.250 1.1585 0.18052 0.17443 -0.1583 0.2551 1.0000
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Polar data table (+)
Polar graphs
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