EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 50,000 Max Cl/Cd: 32.81 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e555-il-50000-n5.txt Download as CSV file: xf-e555-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5167 0.10082 0.09322 -0.0560 1.0000 0.0407
-12.500 -0.5420 0.09246 0.08479 -0.0604 1.0000 0.0401
-12.250 -0.5662 0.08528 0.07749 -0.0641 1.0000 0.0395
-12.000 -0.5888 0.07903 0.07111 -0.0670 1.0000 0.0393
-11.750 -0.6071 0.07385 0.06578 -0.0689 1.0000 0.0392
-11.500 -0.6210 0.06952 0.06128 -0.0699 1.0000 0.0392
-11.250 -0.6314 0.06574 0.05734 -0.0704 1.0000 0.0394
-11.000 -0.6389 0.06238 0.05382 -0.0702 1.0000 0.0400
-10.750 -0.6442 0.05940 0.05063 -0.0696 1.0000 0.0409
-10.500 -0.6473 0.05668 0.04769 -0.0686 1.0000 0.0421
-10.250 -0.6490 0.05420 0.04492 -0.0672 1.0000 0.0434
-10.000 -0.6382 0.05266 0.04348 -0.0656 1.0000 0.0457
-9.750 -0.6291 0.05109 0.04183 -0.0636 1.0000 0.0483
-9.500 -0.6138 0.04971 0.04019 -0.0612 1.0000 0.0515
-9.250 -0.6044 0.04856 0.03914 -0.0588 1.0000 0.0547
-9.000 -0.6000 0.04735 0.03792 -0.0563 1.0000 0.0587
-8.750 -0.5957 0.04624 0.03675 -0.0533 1.0000 0.0631
-8.500 -0.6006 0.04502 0.03565 -0.0502 1.0000 0.0670
-8.250 -0.6060 0.04392 0.03452 -0.0466 1.0000 0.0713
-8.000 -0.6138 0.04263 0.03331 -0.0433 1.0000 0.0756
-7.750 -0.6212 0.04117 0.03191 -0.0405 1.0000 0.0811
-7.500 -0.6272 0.03964 0.03042 -0.0380 1.0000 0.0877
-7.250 -0.6322 0.03801 0.02884 -0.0358 1.0000 0.0962
-7.000 -0.6359 0.03617 0.02712 -0.0341 1.0000 0.1078
-6.750 -0.6362 0.03410 0.02518 -0.0331 1.0000 0.1265
-6.500 -0.6337 0.03138 0.02284 -0.0336 1.0000 0.1619
-6.250 -0.6139 0.02992 0.02293 -0.0350 0.9944 0.3082
-6.000 -0.5750 0.03108 0.02384 -0.0373 0.9858 0.4030
-5.750 -0.5398 0.03286 0.02535 -0.0374 0.9770 0.4409
-5.500 -0.5062 0.03436 0.02660 -0.0372 0.9685 0.4669
-5.250 -0.4729 0.03590 0.02796 -0.0362 0.9605 0.4863
-5.000 -0.4438 0.03675 0.02862 -0.0353 0.9515 0.5023
-4.500 -0.3796 0.03649 0.02783 -0.0381 0.9347 0.5290
-4.250 -0.3494 0.03661 0.02780 -0.0379 0.9266 0.5344
-4.000 -0.3150 0.03577 0.02666 -0.0410 0.9183 0.5440
-3.750 -0.2861 0.03549 0.02622 -0.0415 0.9094 0.5488
-3.500 -0.2510 0.03507 0.02562 -0.0434 0.9020 0.5544
-3.250 -0.2200 0.03416 0.02444 -0.0463 0.8924 0.5619
-3.000 -0.1840 0.03389 0.02404 -0.0478 0.8857 0.5656
-2.750 -0.1569 0.03352 0.02354 -0.0484 0.8757 0.5701
-2.500 -0.1158 0.03280 0.02259 -0.0522 0.8695 0.5764
-2.250 -0.0893 0.03247 0.02215 -0.0527 0.8591 0.5806
-2.000 -0.0502 0.03208 0.02165 -0.0549 0.8532 0.5845
-1.750 -0.0240 0.03176 0.02122 -0.0555 0.8425 0.5892
-1.500 0.0197 0.03115 0.02044 -0.0594 0.8369 0.5951
-1.250 0.0428 0.03104 0.02029 -0.0588 0.8257 0.5985
-1.000 0.0846 0.03064 0.01980 -0.0615 0.8203 0.6028
-0.750 0.1100 0.03043 0.01951 -0.0620 0.8089 0.6079
-0.500 0.1447 0.03012 0.01913 -0.0637 0.8009 0.6127
-0.250 0.1746 0.02995 0.01894 -0.0642 0.7918 0.6166
0.000 0.2043 0.02978 0.01872 -0.0649 0.7823 0.6213
0.250 0.2419 0.02943 0.01828 -0.0673 0.7744 0.6273
0.500 0.2660 0.02941 0.01830 -0.0667 0.7638 0.6310
0.750 0.3031 0.02912 0.01798 -0.0682 0.7569 0.6360
1.000 0.3289 0.02911 0.01795 -0.0686 0.7455 0.6415
1.250 0.3652 0.02885 0.01768 -0.0700 0.7382 0.6463
1.500 0.3894 0.02889 0.01777 -0.0695 0.7271 0.6511
1.750 0.4185 0.02887 0.01774 -0.0702 0.7172 0.6572
2.000 0.4528 0.02868 0.01757 -0.0712 0.7090 0.6625
2.250 0.4756 0.02883 0.01778 -0.0706 0.6977 0.6677
2.500 0.5132 0.02860 0.01754 -0.0723 0.6901 0.6746
2.750 0.5356 0.02877 0.01779 -0.0715 0.6787 0.6799
3.000 0.5614 0.02888 0.01798 -0.0713 0.6683 0.6862
3.250 0.5967 0.02873 0.01785 -0.0725 0.6599 0.6933
3.500 0.6168 0.02901 0.01824 -0.0714 0.6483 0.6994
3.750 0.6472 0.02904 0.01833 -0.0720 0.6387 0.7073
4.000 0.6742 0.02908 0.01847 -0.0716 0.6288 0.7142
4.250 0.6972 0.02936 0.01885 -0.0711 0.6173 0.7224
4.500 0.7269 0.02931 0.01891 -0.0711 0.6081 0.7303
4.750 0.7523 0.02950 0.01919 -0.0709 0.5969 0.7398
5.000 0.7722 0.02978 0.01963 -0.0696 0.5854 0.7484
5.250 0.8010 0.02979 0.01975 -0.0695 0.5753 0.7589
5.500 0.8256 0.02990 0.01998 -0.0689 0.5641 0.7699
5.750 0.8436 0.03022 0.02047 -0.0673 0.5519 0.7813
6.000 0.8661 0.03036 0.02077 -0.0663 0.5405 0.7946
6.250 0.8954 0.03017 0.02069 -0.0659 0.5300 0.8096
6.500 0.9094 0.03055 0.02126 -0.0637 0.5170 0.8267
6.750 0.9249 0.03081 0.02173 -0.0616 0.5045 0.8476
7.000 0.9429 0.03086 0.02196 -0.0597 0.4924 0.8764
7.250 0.9677 0.03076 0.02203 -0.0589 0.4797 0.9336
7.500 0.9974 0.03097 0.02231 -0.0597 0.4652 1.0000
7.750 1.0237 0.03137 0.02276 -0.0600 0.4503 1.0000
8.000 1.0452 0.03191 0.02336 -0.0595 0.4349 1.0000
8.250 1.0651 0.03246 0.02397 -0.0587 0.4193 1.0000
8.500 1.0832 0.03305 0.02462 -0.0576 0.4035 1.0000
8.750 1.0987 0.03367 0.02528 -0.0561 0.3875 1.0000
9.000 1.1121 0.03435 0.02601 -0.0543 0.3715 1.0000
9.250 1.1243 0.03511 0.02679 -0.0525 0.3552 1.0000
9.500 1.1330 0.03607 0.02779 -0.0503 0.3387 1.0000
9.750 1.1403 0.03716 0.02894 -0.0482 0.3222 1.0000
10.000 1.1465 0.03837 0.03020 -0.0462 0.3058 1.0000
10.250 1.1514 0.03974 0.03161 -0.0442 0.2895 1.0000
10.500 1.1555 0.04124 0.03314 -0.0424 0.2736 1.0000
10.750 1.1588 0.04289 0.03482 -0.0407 0.2580 1.0000
11.000 1.1619 0.04468 0.03663 -0.0392 0.2431 1.0000
11.250 1.1641 0.04663 0.03860 -0.0379 0.2288 1.0000
11.500 1.1664 0.04869 0.04064 -0.0368 0.2153 1.0000
11.750 1.1674 0.05097 0.04294 -0.0358 0.2023 1.0000
12.000 1.1668 0.05359 0.04564 -0.0351 0.1900 1.0000
12.250 1.1665 0.05630 0.04841 -0.0345 0.1786 1.0000
12.500 1.1668 0.05899 0.05112 -0.0341 0.1680 1.0000
12.750 1.1682 0.06162 0.05373 -0.0338 0.1582 1.0000
13.000 1.1649 0.06505 0.05732 -0.0338 0.1489 1.0000
13.250 1.1650 0.06804 0.06034 -0.0338 0.1404 1.0000
13.500 1.1631 0.07144 0.06386 -0.0341 0.1324 1.0000
13.750 1.1610 0.07498 0.06749 -0.0345 0.1252 1.0000
14.000 1.1590 0.07854 0.07114 -0.0351 0.1183 1.0000
14.250 1.1565 0.08237 0.07507 -0.0359 0.1123 1.0000
14.500 1.1504 0.08683 0.07971 -0.0371 0.1066 1.0000
14.750 1.1527 0.08993 0.08277 -0.0377 0.1011 1.0000
15.000 1.1396 0.09601 0.08917 -0.0400 0.0971 1.0000
15.250 1.1342 0.10068 0.09396 -0.0418 0.0927 1.0000
15.500 1.1350 0.10427 0.09756 -0.0429 0.0883 1.0000
15.750 1.1133 0.11257 0.10618 -0.0471 0.0862 1.0000
16.000 1.0866 0.12238 0.11627 -0.0525 0.0846 1.0000
16.250 1.0416 0.13736 0.13146 -0.0614 0.0842 1.0000
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Polar data table (+)
Polar graphs
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