EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 100,000 Max Cl/Cd: 50.61 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e407-il-100000.txt Download as CSV file: xf-e407-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 407 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4393 0.11619 0.11222 -0.0344 1.0000 0.1280
-9.500 -0.4867 0.11447 0.11008 -0.0333 1.0000 0.1242
-9.250 -0.5606 0.10923 0.10506 -0.0409 1.0000 0.1282
-8.500 -0.4617 0.09771 0.09390 -0.0308 1.0000 0.1446
-8.250 -0.4593 0.09464 0.09085 -0.0290 1.0000 0.1470
-8.000 -0.4705 0.09059 0.08685 -0.0287 1.0000 0.1489
-7.750 -0.4895 0.08588 0.08220 -0.0290 1.0000 0.1506
-7.500 -0.5249 0.08090 0.07731 -0.0297 1.0000 0.1598
-7.250 -0.5446 0.07668 0.07314 -0.0289 1.0000 0.1612
-7.000 -0.5729 0.07290 0.06943 -0.0274 1.0000 0.1635
-6.750 -0.6883 0.04912 0.04227 -0.0486 1.0000 0.0472
-6.500 -0.6711 0.04425 0.03714 -0.0492 1.0000 0.0459
-6.250 -0.6495 0.04053 0.03297 -0.0496 1.0000 0.0452
-6.000 -0.6259 0.03755 0.02956 -0.0498 1.0000 0.0451
-5.750 -0.6018 0.03535 0.02696 -0.0496 1.0000 0.0460
-5.500 -0.5788 0.03301 0.02444 -0.0495 1.0000 0.0503
-5.250 -0.5560 0.03154 0.02288 -0.0489 1.0000 0.0543
-5.000 -0.5326 0.03019 0.02132 -0.0480 1.0000 0.0585
-4.750 -0.5096 0.02876 0.02000 -0.0476 1.0000 0.0690
-4.500 -0.4845 0.02753 0.01882 -0.0475 1.0000 0.0858
-4.250 -0.4549 0.02601 0.01768 -0.0491 1.0000 0.1252
-4.000 -0.4114 0.02362 0.01801 -0.0541 1.0000 0.5361
-3.750 -0.3965 0.02491 0.01916 -0.0507 1.0000 0.5906
-3.500 -0.3857 0.02622 0.02036 -0.0463 1.0000 0.6189
-3.250 -0.3799 0.02748 0.02161 -0.0405 1.0000 0.6378
-3.000 -0.3716 0.02854 0.02261 -0.0356 1.0000 0.6560
-2.750 -0.3597 0.02939 0.02336 -0.0318 1.0000 0.6746
-2.500 -0.3486 0.03011 0.02398 -0.0281 1.0000 0.6906
-2.250 -0.3381 0.03069 0.02449 -0.0243 1.0000 0.7050
-2.000 -0.3283 0.03116 0.02491 -0.0204 1.0000 0.7181
-1.750 -0.3192 0.03152 0.02519 -0.0165 1.0000 0.7302
-1.500 -0.3079 0.03180 0.02540 -0.0134 1.0000 0.7424
-1.250 -0.2949 0.03202 0.02555 -0.0109 1.0000 0.7545
-1.000 -0.2798 0.03222 0.02567 -0.0090 1.0000 0.7664
-0.750 -0.2616 0.03244 0.02580 -0.0082 1.0000 0.7780
-0.500 -0.2294 0.03342 0.02664 -0.0097 0.9941 0.7884
-0.250 -0.1449 0.03507 0.02804 -0.0201 0.9524 0.7960
0.000 -0.1028 0.03539 0.02822 -0.0238 0.9396 0.8018
0.250 -0.0569 0.03583 0.02854 -0.0284 0.9299 0.8066
0.500 -0.0268 0.03582 0.02847 -0.0296 0.9193 0.8107
0.750 0.0063 0.03590 0.02848 -0.0317 0.9088 0.8150
1.000 0.0494 0.03622 0.02871 -0.0360 0.8999 0.8194
1.250 0.0830 0.03630 0.02877 -0.0375 0.8914 0.8230
1.500 0.1114 0.03634 0.02879 -0.0386 0.8810 0.8270
1.750 0.1514 0.03655 0.02896 -0.0419 0.8725 0.8311
2.000 0.1912 0.03667 0.02907 -0.0450 0.8640 0.8346
2.250 0.2171 0.03666 0.02907 -0.0453 0.8534 0.8383
2.500 0.2572 0.03673 0.02915 -0.0481 0.8459 0.8423
2.750 0.2950 0.03676 0.02920 -0.0508 0.8365 0.8461
3.000 0.3252 0.03673 0.02921 -0.0519 0.8257 0.8498
3.250 0.3712 0.03646 0.02898 -0.0549 0.8204 0.8537
3.500 0.3997 0.03638 0.02896 -0.0558 0.8086 0.8575
3.750 0.4338 0.03633 0.02898 -0.0577 0.7976 0.8615
4.000 0.4768 0.03574 0.02848 -0.0598 0.7915 0.8655
4.250 0.5077 0.03542 0.02824 -0.0606 0.7804 0.8697
4.500 0.5412 0.03513 0.02806 -0.0619 0.7688 0.8738
4.750 0.5917 0.03408 0.02713 -0.0649 0.7638 0.8780
5.000 0.6217 0.03349 0.02668 -0.0649 0.7520 0.8827
5.250 0.6564 0.03282 0.02614 -0.0658 0.7400 0.8875
5.500 0.7113 0.03105 0.02453 -0.0688 0.7357 0.8917
5.750 0.7439 0.02997 0.02363 -0.0687 0.7237 0.8966
6.000 0.7807 0.02875 0.02258 -0.0692 0.7118 0.9022
6.500 0.8678 0.02509 0.01932 -0.0710 0.6885 0.9132
6.750 0.9130 0.02342 0.01782 -0.0723 0.6701 0.9188
7.000 0.9529 0.02198 0.01651 -0.0727 0.6448 0.9255
7.250 0.9956 0.02088 0.01543 -0.0739 0.6084 0.9322
7.500 1.0250 0.02046 0.01496 -0.0733 0.5637 0.9400
7.750 1.0441 0.02063 0.01500 -0.0716 0.5151 0.9490
8.000 1.0590 0.02108 0.01525 -0.0694 0.4648 0.9611
8.250 1.0705 0.02175 0.01573 -0.0672 0.4131 0.9969
8.500 1.0831 0.02301 0.01670 -0.0658 0.3597 1.0000
8.750 1.0929 0.02447 0.01791 -0.0642 0.3078 1.0000
9.000 1.1016 0.02616 0.01928 -0.0627 0.2599 1.0000
9.250 1.1103 0.02801 0.02086 -0.0614 0.2151 1.0000
9.500 1.1195 0.03002 0.02265 -0.0602 0.1765 1.0000
9.750 1.1299 0.03215 0.02454 -0.0591 0.1443 1.0000
10.000 1.1422 0.03435 0.02650 -0.0584 0.1194 1.0000
10.250 1.1579 0.03640 0.02858 -0.0579 0.0994 1.0000
10.500 1.1788 0.03859 0.03070 -0.0578 0.0850 1.0000
10.750 1.2016 0.04080 0.03293 -0.0581 0.0734 1.0000
11.000 1.2358 0.04348 0.03562 -0.0594 0.0643 1.0000
11.250 1.2583 0.04575 0.03794 -0.0597 0.0574 1.0000
11.500 1.2878 0.04932 0.04188 -0.0604 0.0520 1.0000
11.750 1.3027 0.05214 0.04498 -0.0596 0.0482 1.0000
12.000 1.3243 0.05670 0.04958 -0.0605 0.0437 1.0000
12.250 1.3199 0.05980 0.05315 -0.0578 0.0427 1.0000
12.500 1.3134 0.06367 0.05746 -0.0553 0.0420 1.0000
12.750 1.3024 0.06780 0.06200 -0.0529 0.0414 1.0000
13.000 1.2876 0.07213 0.06671 -0.0508 0.0410 1.0000
13.250 1.2699 0.07678 0.07170 -0.0493 0.0406 1.0000
13.500 1.2501 0.08181 0.07704 -0.0484 0.0405 1.0000
13.750 1.2282 0.08731 0.08284 -0.0483 0.0405 1.0000
14.000 1.2046 0.09337 0.08917 -0.0492 0.0407 1.0000
14.250 1.1799 0.10005 0.09610 -0.0511 0.0411 1.0000
14.500 1.1550 0.10738 0.10365 -0.0543 0.0416 1.0000
14.750 1.1311 0.11537 0.11181 -0.0585 0.0423 1.0000
15.000 1.1086 0.12400 0.12058 -0.0636 0.0430 1.0000
15.250 1.0894 0.13297 0.12963 -0.0691 0.0436 1.0000
15.500 0.7753 0.15590 0.15321 -0.0713 0.0684 1.0000
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Polar data table (+)
Polar graphs
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