EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 100,000 Max Cl/Cd: 68.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e58-il-100000-n5.txt Download as CSV file: xf-e58-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3067 0.10775 0.10318 -0.0343 0.9799 0.0295
-6.500 -0.3028 0.10526 0.10072 -0.0343 0.9769 0.0300
-6.250 -0.2998 0.10287 0.09836 -0.0345 0.9734 0.0305
-6.000 -0.2893 0.09993 0.09543 -0.0368 0.9704 0.0310
-5.750 -0.2805 0.09710 0.09262 -0.0386 0.9671 0.0315
-5.500 -0.2719 0.09415 0.08970 -0.0404 0.9629 0.0325
-5.250 -0.2564 0.09082 0.08637 -0.0441 0.9594 0.0331
-5.000 -0.2388 0.08733 0.08287 -0.0485 0.9561 0.0339
-4.750 -0.2247 0.08402 0.07958 -0.0518 0.9510 0.0347
-4.500 -0.1985 0.07993 0.07544 -0.0585 0.9472 0.0355
-4.250 -0.1337 0.07396 0.06933 -0.0790 0.9443 0.0380
-3.250 0.0335 0.05169 0.04659 -0.1138 0.9336 0.0267
-3.000 0.1204 0.04331 0.03775 -0.1332 0.9351 0.0266
-2.750 0.2066 0.03633 0.03007 -0.1505 0.9377 0.0308
-2.500 0.2908 0.03080 0.02336 -0.1647 0.9416 0.0345
-2.250 0.3432 0.02837 0.02015 -0.1706 0.9419 0.0407
-2.000 0.3789 0.02742 0.01887 -0.1727 0.9395 0.0477
-1.750 0.4162 0.02642 0.01758 -0.1749 0.9377 0.0538
-1.500 0.4511 0.02592 0.01693 -0.1766 0.9355 0.0603
-1.250 0.4867 0.02558 0.01648 -0.1784 0.9335 0.0690
-1.000 0.5235 0.02534 0.01610 -0.1803 0.9318 0.0750
-0.750 0.5558 0.02520 0.01597 -0.1815 0.9288 0.0896
-0.500 0.5830 0.02521 0.01606 -0.1816 0.9241 0.1407
-0.250 0.6151 0.02526 0.01610 -0.1827 0.9208 0.1874
0.000 0.6497 0.02529 0.01612 -0.1842 0.9183 0.2206
0.250 0.6765 0.02532 0.01623 -0.1843 0.9127 0.2561
0.500 0.7098 0.02511 0.01631 -0.1858 0.9079 0.3447
0.750 0.7393 0.02395 0.01633 -0.1856 0.9047 0.8435
1.000 0.7631 0.02389 0.01619 -0.1847 0.8957 1.0000
1.250 0.8007 0.02377 0.01595 -0.1864 0.8911 1.0000
1.500 0.8272 0.02378 0.01590 -0.1861 0.8822 1.0000
1.750 0.8649 0.02356 0.01563 -0.1877 0.8774 1.0000
2.000 0.8897 0.02359 0.01567 -0.1870 0.8678 1.0000
2.250 0.9291 0.02320 0.01528 -0.1888 0.8632 1.0000
2.500 0.9532 0.02317 0.01529 -0.1879 0.8523 1.0000
2.750 0.9800 0.02303 0.01524 -0.1874 0.8418 1.0000
3.000 1.0102 0.02272 0.01499 -0.1874 0.8321 1.0000
3.250 1.0436 0.02222 0.01459 -0.1878 0.8231 1.0000
3.500 1.0678 0.02208 0.01460 -0.1867 0.8101 1.0000
3.750 1.0918 0.02198 0.01462 -0.1856 0.7966 1.0000
4.250 1.1415 0.02173 0.01466 -0.1835 0.7635 1.0000
4.500 1.1682 0.02156 0.01468 -0.1828 0.7446 1.0000
4.750 1.2045 0.02075 0.01401 -0.1831 0.7152 1.0000
5.000 1.2683 0.01898 0.01219 -0.1877 0.6572 1.0000
5.250 1.3191 0.01928 0.01151 -0.1905 0.4837 1.0000
5.500 1.3295 0.02079 0.01237 -0.1871 0.3846 1.0000
5.750 1.3343 0.02270 0.01348 -0.1833 0.2665 1.0000
6.000 1.3428 0.02468 0.01474 -0.1803 0.1624 1.0000
6.250 1.3495 0.02716 0.01643 -0.1772 0.0548 1.0000
6.500 1.3628 0.02884 0.01797 -0.1746 0.0278 1.0000
6.750 1.3774 0.03030 0.01951 -0.1723 0.0220 1.0000
7.000 1.3905 0.03188 0.02136 -0.1697 0.0196 1.0000
7.250 1.4001 0.03378 0.02349 -0.1666 0.0182 1.0000
7.500 1.4092 0.03565 0.02559 -0.1635 0.0172 1.0000
7.750 1.4198 0.03744 0.02762 -0.1607 0.0160 1.0000
8.000 1.4306 0.03945 0.02984 -0.1580 0.0148 1.0000
8.250 1.4437 0.04173 0.03232 -0.1556 0.0143 1.0000
8.500 1.4622 0.04428 0.03509 -0.1539 0.0138 1.0000
8.750 1.4862 0.04726 0.03835 -0.1530 0.0133 1.0000
9.000 1.5108 0.05060 0.04204 -0.1523 0.0130 1.0000
9.250 1.5258 0.05385 0.04567 -0.1504 0.0123 1.0000
9.500 1.5316 0.05696 0.04912 -0.1476 0.0115 1.0000
9.750 1.5348 0.06047 0.05300 -0.1445 0.0112 1.0000
10.000 1.5329 0.06413 0.05711 -0.1411 0.0109 1.0000
10.250 1.5269 0.06809 0.06144 -0.1376 0.0107 1.0000
10.500 1.5177 0.07222 0.06595 -0.1339 0.0107 1.0000
10.750 1.5060 0.07648 0.07058 -0.1306 0.0107 1.0000
11.000 1.4928 0.08086 0.07532 -0.1277 0.0108 1.0000
11.250 1.4766 0.08574 0.08054 -0.1253 0.0108 1.0000
11.500 1.4591 0.09089 0.08600 -0.1237 0.0108 1.0000
11.750 1.4409 0.09645 0.09187 -0.1230 0.0109 1.0000
12.000 1.4222 0.10238 0.09809 -0.1233 0.0110 1.0000
12.250 1.4027 0.10893 0.10491 -0.1250 0.0111 1.0000
12.500 1.3833 0.11608 0.11229 -0.1279 0.0111 1.0000
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Polar data table (+)
Polar graphs
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