E591 (e591-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: E591 (e591-il) Reynolds number: 50,000 Max Cl/Cd: 34.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e591-il-50000-n5.txt Download as CSV file: xf-e591-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2174 0.15029 0.14346 -0.0355 1.0000 0.1088
-10.750 -0.2294 0.14974 0.14302 -0.0353 1.0000 0.1097
-10.500 -0.2413 0.14909 0.14249 -0.0348 1.0000 0.1101
-10.250 -0.2270 0.14471 0.13818 -0.0326 1.0000 0.1116
-10.000 -0.2252 0.14261 0.13615 -0.0308 1.0000 0.1132
-9.750 -0.2279 0.14096 0.13460 -0.0293 1.0000 0.1143
-9.500 -0.2248 0.13867 0.13236 -0.0297 0.9984 0.1157
-9.250 -0.2075 0.13487 0.12856 -0.0342 0.9928 0.1173
-9.000 -0.1920 0.13102 0.12471 -0.0383 0.9866 0.1177
-8.500 -0.1756 0.11820 0.11177 -0.0499 0.9735 0.0675
-8.250 -0.1761 0.11244 0.10604 -0.0556 0.9644 0.0625
-8.000 -0.1612 0.10884 0.10243 -0.0582 0.9563 0.0617
-7.750 -0.1474 0.10480 0.09840 -0.0621 0.9490 0.0613
-7.500 -0.1404 0.10096 0.09459 -0.0651 0.9390 0.0612
-7.250 -0.1355 0.09718 0.09083 -0.0679 0.9285 0.0612
-7.000 -0.1308 0.09298 0.08666 -0.0713 0.9192 0.0613
-6.750 -0.1278 0.08916 0.08287 -0.0740 0.9086 0.0610
-6.500 -0.1302 0.08543 0.07918 -0.0759 0.8960 0.0608
-6.250 -0.1266 0.08031 0.07407 -0.0804 0.8854 0.0604
-6.000 -0.1227 0.07351 0.06724 -0.0875 0.8747 0.0596
-5.750 -0.1250 0.06269 0.05620 -0.1016 0.8610 0.0583
-5.500 -0.0905 0.05176 0.04450 -0.1199 0.8549 0.0584
-5.250 -0.0642 0.04724 0.03944 -0.1260 0.8438 0.0599
-5.000 -0.0170 0.04295 0.03448 -0.1337 0.8386 0.0636
-4.750 0.0144 0.04107 0.03238 -0.1360 0.8297 0.0666
-4.500 0.0552 0.03851 0.02927 -0.1397 0.8227 0.0701
-4.250 0.0984 0.03676 0.02741 -0.1428 0.8181 0.0759
-4.000 0.1242 0.03572 0.02621 -0.1432 0.8071 0.0808
-3.750 0.1659 0.03422 0.02454 -0.1457 0.8013 0.0890
-3.500 0.2012 0.03312 0.02334 -0.1472 0.7933 0.0991
-3.250 0.2363 0.03210 0.02234 -0.1489 0.7847 0.1129
-3.000 0.2858 0.03060 0.02096 -0.1530 0.7800 0.1437
-2.750 0.3171 0.03001 0.02064 -0.1545 0.7688 0.1935
-2.500 0.3630 0.02958 0.02033 -0.1575 0.7624 0.2751
-2.250 0.3919 0.02988 0.02068 -0.1575 0.7522 0.3233
-2.000 0.4280 0.02991 0.02064 -0.1582 0.7441 0.3641
-1.750 0.4601 0.02996 0.02060 -0.1584 0.7354 0.3951
-1.500 0.4918 0.02992 0.02041 -0.1587 0.7257 0.4209
-1.250 0.5313 0.02957 0.01989 -0.1601 0.7188 0.4436
-1.000 0.5538 0.02973 0.02000 -0.1590 0.7073 0.4591
-0.750 0.5967 0.02925 0.01933 -0.1608 0.7012 0.4793
-0.500 0.6162 0.02956 0.01958 -0.1595 0.6887 0.4934
-0.250 0.6576 0.02914 0.01898 -0.1611 0.6821 0.5129
0.000 0.6782 0.02949 0.01926 -0.1601 0.6701 0.5287
0.250 0.7175 0.02915 0.01877 -0.1614 0.6630 0.5485
0.500 0.7371 0.02953 0.01912 -0.1601 0.6515 0.5646
0.750 0.7736 0.02930 0.01877 -0.1610 0.6441 0.5853
1.000 0.7931 0.02967 0.01916 -0.1596 0.6332 0.6026
1.250 0.8270 0.02953 0.01892 -0.1602 0.6253 0.6256
1.500 0.8476 0.02991 0.01930 -0.1590 0.6153 0.6464
1.750 0.8762 0.02988 0.01925 -0.1586 0.6070 0.6708
2.000 0.8976 0.03014 0.01953 -0.1573 0.5979 0.6963
2.250 0.9212 0.03030 0.01970 -0.1563 0.5892 0.7264
2.500 0.9458 0.03027 0.01968 -0.1552 0.5818 0.7619
2.750 0.9565 0.03066 0.02018 -0.1522 0.5722 0.8024
3.000 0.9773 0.03023 0.01977 -0.1499 0.5660 0.8805
3.250 0.9935 0.03097 0.02050 -0.1488 0.5557 1.0000
3.500 1.0323 0.03118 0.02047 -0.1508 0.5482 1.0000
3.750 1.0541 0.03201 0.02122 -0.1505 0.5390 1.0000
4.000 1.0834 0.03249 0.02156 -0.1510 0.5310 1.0000
4.250 1.1126 0.03297 0.02190 -0.1513 0.5235 1.0000
4.500 1.1300 0.03388 0.02280 -0.1502 0.5144 1.0000
4.750 1.1679 0.03396 0.02269 -0.1516 0.5083 1.0000
5.000 1.1751 0.03532 0.02411 -0.1491 0.4989 1.0000
5.250 1.2043 0.03570 0.02439 -0.1493 0.4918 1.0000
5.500 1.2235 0.03655 0.02523 -0.1484 0.4843 1.0000
5.750 1.2372 0.03759 0.02628 -0.1467 0.4763 1.0000
6.000 1.2756 0.03762 0.02616 -0.1480 0.4705 1.0000
6.250 1.2709 0.03943 0.02810 -0.1441 0.4617 1.0000
6.500 1.2952 0.04001 0.02865 -0.1437 0.4550 1.0000
6.750 1.3191 0.04065 0.02925 -0.1432 0.4488 1.0000
7.000 1.3143 0.04264 0.03136 -0.1396 0.4404 1.0000
7.250 1.3471 0.04276 0.03140 -0.1401 0.4346 1.0000
7.500 1.3443 0.04480 0.03357 -0.1369 0.4273 1.0000
7.750 1.3487 0.04651 0.03535 -0.1347 0.4201 1.0000
8.000 1.3895 0.04610 0.03483 -0.1357 0.4151 1.0000
8.250 1.3548 0.05037 0.03935 -0.1304 0.4063 1.0000
8.500 1.3703 0.05151 0.04050 -0.1294 0.4002 1.0000
8.750 1.4192 0.05036 0.03926 -0.1307 0.3961 1.0000
9.000 1.3408 0.05892 0.04819 -0.1245 0.3848 1.0000
9.250 1.3771 0.05822 0.04745 -0.1244 0.3805 1.0000
9.500 1.2936 0.06990 0.05943 -0.1218 0.3670 1.0000
9.750 1.3236 0.06947 0.05900 -0.1211 0.3632 1.0000
10.000 1.3730 0.06694 0.05641 -0.1207 0.3609 1.0000
10.500 1.3190 0.07990 0.06964 -0.1198 0.3431 1.0000
11.000 1.2741 0.09373 0.08369 -0.1213 0.3249 1.0000
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Polar data table (+)
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