E591 (e591-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E591 (e591-il) Reynolds number: 200,000 Max Cl/Cd: 77.22 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e591-il-200000.txt Download as CSV file: xf-e591-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.0147 0.09173 0.08837 -0.0863 0.9429 0.0653
-7.750 -0.0292 0.08469 0.08139 -0.0985 0.9315 0.0701
-7.500 0.0048 0.08255 0.07923 -0.0968 0.9286 0.0711
-7.250 0.0325 0.07973 0.07640 -0.0991 0.9251 0.0729
-7.000 0.0095 0.07227 0.06899 -0.1104 0.9102 0.0787
-6.750 -0.0233 0.03586 0.03115 -0.1562 0.8918 0.0436
-6.500 0.0080 0.03200 0.02704 -0.1604 0.8850 0.0426
-6.250 0.0498 0.02788 0.02230 -0.1666 0.8791 0.0427
-6.000 0.1025 0.02478 0.01850 -0.1732 0.8761 0.0437
-5.750 0.1541 0.02223 0.01564 -0.1785 0.8733 0.0445
-5.500 0.1844 0.02096 0.01432 -0.1791 0.8631 0.0457
-5.250 0.2304 0.01952 0.01271 -0.1826 0.8573 0.0476
-5.000 0.2673 0.01840 0.01141 -0.1843 0.8479 0.0500
-4.750 0.3070 0.01753 0.01052 -0.1866 0.8390 0.0542
-4.500 0.3408 0.01669 0.00968 -0.1877 0.8279 0.0580
-4.250 0.3809 0.01587 0.00878 -0.1900 0.8183 0.0636
-4.000 0.4108 0.01533 0.00825 -0.1904 0.8053 0.0713
-3.750 0.4478 0.01470 0.00762 -0.1923 0.7944 0.0837
-3.500 0.4825 0.01397 0.00696 -0.1939 0.7820 0.1137
-3.250 0.5167 0.01325 0.00667 -0.1958 0.7693 0.2352
-3.000 0.5499 0.01328 0.00662 -0.1965 0.7579 0.2809
-2.750 0.5772 0.01337 0.00665 -0.1962 0.7446 0.3074
-2.500 0.6058 0.01348 0.00667 -0.1960 0.7321 0.3292
-2.250 0.6366 0.01362 0.00667 -0.1962 0.7207 0.3511
-2.000 0.6619 0.01376 0.00680 -0.1954 0.7076 0.3718
-1.750 0.6903 0.01388 0.00683 -0.1952 0.6960 0.3894
-1.500 0.7182 0.01396 0.00681 -0.1950 0.6842 0.4053
-1.250 0.7450 0.01408 0.00685 -0.1945 0.6722 0.4211
-1.000 0.7740 0.01416 0.00684 -0.1945 0.6617 0.4343
-0.750 0.7993 0.01420 0.00685 -0.1938 0.6496 0.4471
-0.500 0.8275 0.01431 0.00686 -0.1936 0.6391 0.4605
-0.250 0.8537 0.01436 0.00689 -0.1931 0.6279 0.4728
0.000 0.8812 0.01449 0.00692 -0.1929 0.6176 0.4867
0.250 0.9078 0.01458 0.00698 -0.1924 0.6072 0.5004
0.500 0.9344 0.01469 0.00707 -0.1920 0.5971 0.5142
0.750 0.9615 0.01481 0.00713 -0.1917 0.5874 0.5297
1.000 0.9879 0.01497 0.00725 -0.1913 0.5776 0.5463
1.250 1.0143 0.01508 0.00735 -0.1908 0.5683 0.5625
1.500 1.0403 0.01524 0.00752 -0.1903 0.5591 0.5803
1.750 1.0661 0.01537 0.00764 -0.1898 0.5500 0.5992
2.000 1.0923 0.01555 0.00782 -0.1894 0.5414 0.6201
2.250 1.1173 0.01569 0.00799 -0.1887 0.5325 0.6428
2.500 1.1442 0.01591 0.00816 -0.1884 0.5246 0.6679
2.750 1.1673 0.01602 0.00839 -0.1873 0.5158 0.6937
3.000 1.1938 0.01624 0.00855 -0.1869 0.5082 0.7251
3.250 1.2151 0.01636 0.00882 -0.1855 0.5000 0.7582
3.500 1.2370 0.01648 0.00899 -0.1841 0.4924 0.7996
3.750 1.2542 0.01656 0.00914 -0.1816 0.4855 0.8567
4.000 1.2680 0.01647 0.00915 -0.1786 0.4780 1.0000
4.250 1.2979 0.01684 0.00933 -0.1792 0.4708 1.0000
4.500 1.3226 0.01715 0.00964 -0.1787 0.4629 1.0000
4.750 1.3482 0.01746 0.00987 -0.1784 0.4554 1.0000
5.000 1.3748 0.01786 0.01017 -0.1783 0.4485 1.0000
5.250 1.3976 0.01817 0.01050 -0.1774 0.4408 1.0000
5.500 1.4238 0.01855 0.01075 -0.1772 0.4341 1.0000
5.750 1.4464 0.01891 0.01114 -0.1763 0.4270 1.0000
6.000 1.4689 0.01925 0.01145 -0.1754 0.4199 1.0000
6.250 1.4956 0.01971 0.01179 -0.1754 0.4135 1.0000
6.500 1.5145 0.02005 0.01222 -0.1738 0.4064 1.0000
6.750 1.5367 0.02043 0.01255 -0.1729 0.3999 1.0000
7.000 1.5606 0.02091 0.01297 -0.1723 0.3936 1.0000
7.250 1.5787 0.02129 0.01342 -0.1707 0.3868 1.0000
7.500 1.6004 0.02171 0.01378 -0.1697 0.3807 1.0000
7.750 1.6210 0.02220 0.01428 -0.1686 0.3745 1.0000
8.000 1.6364 0.02262 0.01476 -0.1665 0.3681 1.0000
8.250 1.6568 0.02308 0.01515 -0.1654 0.3623 1.0000
8.500 1.6745 0.02362 0.01572 -0.1638 0.3565 1.0000
8.750 1.6884 0.02411 0.01629 -0.1615 0.3504 1.0000
9.000 1.7073 0.02462 0.01674 -0.1602 0.3447 1.0000
9.250 1.7236 0.02524 0.01739 -0.1585 0.3391 1.0000
9.500 1.7359 0.02582 0.01807 -0.1562 0.3333 1.0000
9.750 1.7527 0.02640 0.01861 -0.1546 0.3279 1.0000
10.000 1.7688 0.02711 0.01934 -0.1530 0.3225 1.0000
10.250 1.7787 0.02783 0.02017 -0.1505 0.3169 1.0000
10.500 1.7931 0.02851 0.02085 -0.1487 0.3117 1.0000
10.750 1.8101 0.02929 0.02161 -0.1474 0.3064 1.0000
11.000 1.8169 0.03020 0.02266 -0.1447 0.3011 1.0000
11.250 1.8282 0.03103 0.02354 -0.1427 0.2960 1.0000
11.500 1.8482 0.03182 0.02424 -0.1419 0.2909 1.0000
11.750 1.8507 0.03300 0.02560 -0.1389 0.2860 1.0000
12.000 1.8588 0.03406 0.02673 -0.1368 0.2809 1.0000
12.250 1.8757 0.03492 0.02752 -0.1358 0.2761 1.0000
12.500 1.8804 0.03629 0.02903 -0.1334 0.2714 1.0000
12.750 1.8846 0.03767 0.03054 -0.1312 0.2665 1.0000
13.000 1.8941 0.03886 0.03174 -0.1296 0.2620 1.0000
13.250 1.9069 0.04007 0.03296 -0.1284 0.2573 1.0000
13.500 1.9059 0.04193 0.03500 -0.1261 0.2528 1.0000
13.750 1.9105 0.04353 0.03667 -0.1244 0.2483 1.0000
14.000 1.9274 0.04453 0.03758 -0.1237 0.2437 1.0000
14.250 1.9242 0.04681 0.04007 -0.1217 0.2396 1.0000
14.500 1.9235 0.04898 0.04238 -0.1200 0.2352 1.0000
14.750 1.9288 0.05077 0.04420 -0.1188 0.2310 1.0000
15.000 1.9420 0.05213 0.04553 -0.1181 0.2267 1.0000
15.250 1.9337 0.05519 0.04882 -0.1166 0.2228 1.0000
15.500 1.9331 0.05769 0.05144 -0.1155 0.2186 1.0000
15.750 1.9415 0.05941 0.05314 -0.1148 0.2146 1.0000
16.000 1.9444 0.06183 0.05564 -0.1141 0.2107 1.0000
16.250 1.9353 0.06547 0.05948 -0.1134 0.2068 1.0000
16.500 1.9346 0.06828 0.06238 -0.1129 0.2029 1.0000
16.750 1.9486 0.06952 0.06354 -0.1124 0.1989 1.0000
17.000 1.9390 0.07354 0.06777 -0.1122 0.1954 1.0000
17.250 1.9284 0.07781 0.07223 -0.1123 0.1916 1.0000
17.500 1.9281 0.08083 0.07532 -0.1123 0.1879 1.0000
17.750 1.9493 0.08112 0.07547 -0.1117 0.1838 1.0000
18.000 1.9253 0.08739 0.08205 -0.1126 0.1807 1.0000
18.250 1.9133 0.09223 0.08706 -0.1135 0.1771 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E591 (e591-il)