EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 500,000 Max Cl/Cd: 91.04 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e544-il-500000.txt Download as CSV file: xf-e544-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5900 0.02243 0.01810 -0.0814 0.9518 0.0107
-10.250 -0.5646 0.01779 0.01309 -0.0836 0.9450 0.0092
-10.000 -0.6130 0.02699 0.02141 -0.0774 0.9477 0.0080
-9.750 -0.5709 0.02509 0.01926 -0.0812 0.9426 0.0079
-9.500 -0.5272 0.02332 0.01730 -0.0846 0.9352 0.0079
-9.250 -0.4821 0.02173 0.01559 -0.0884 0.9270 0.0081
-9.000 -0.4428 0.02058 0.01435 -0.0917 0.9121 0.0084
-8.750 -0.4135 0.01972 0.01336 -0.0931 0.8945 0.0087
-8.500 -0.3936 0.01906 0.01258 -0.0926 0.8772 0.0092
-8.000 -0.3642 0.01778 0.01106 -0.0894 0.8484 0.0103
-7.750 -0.3541 0.01703 0.01026 -0.0872 0.8359 0.0111
-7.500 -0.3401 0.01650 0.00965 -0.0855 0.8253 0.0121
-7.250 -0.3268 0.01597 0.00902 -0.0835 0.8150 0.0127
-7.000 -0.3166 0.01531 0.00831 -0.0812 0.8053 0.0140
-6.500 -0.2935 0.01422 0.00714 -0.0767 0.7883 0.0208
-6.250 -0.2868 0.01363 0.00654 -0.0735 0.7808 0.0304
-6.000 -0.2853 0.01306 0.00609 -0.0693 0.7724 0.0533
-5.750 -0.2772 0.01247 0.00565 -0.0664 0.7656 0.0913
-5.500 -0.2676 0.01185 0.00525 -0.0638 0.7585 0.1412
-5.250 -0.2610 0.01099 0.00474 -0.0608 0.7521 0.2268
-5.000 -0.2593 0.00969 0.00404 -0.0572 0.7461 0.3718
-4.750 -0.2567 0.00835 0.00363 -0.0535 0.7400 0.5840
-4.500 -0.2301 0.00857 0.00384 -0.0531 0.7349 0.6326
-4.250 -0.2022 0.00888 0.00409 -0.0529 0.7298 0.6515
-4.000 -0.1747 0.00912 0.00424 -0.0528 0.7244 0.6632
-3.750 -0.1459 0.00941 0.00448 -0.0528 0.7197 0.6708
-3.500 -0.1177 0.00964 0.00461 -0.0528 0.7153 0.6786
-3.250 -0.0888 0.01007 0.00507 -0.0526 0.7106 0.6861
-3.000 -0.0607 0.01047 0.00543 -0.0523 0.7060 0.6951
-2.750 -0.0306 0.01122 0.00619 -0.0519 0.7019 0.7034
-2.500 -0.0033 0.01138 0.00628 -0.0519 0.6975 0.7096
-2.250 0.0245 0.01135 0.00622 -0.0520 0.6932 0.7110
-2.000 0.0525 0.01132 0.00613 -0.0522 0.6893 0.7123
-1.750 0.0811 0.01132 0.00605 -0.0526 0.6855 0.7135
-1.500 0.1088 0.01128 0.00598 -0.0528 0.6815 0.7149
-1.250 0.1365 0.01122 0.00588 -0.0530 0.6775 0.7161
-1.000 0.1646 0.01117 0.00579 -0.0534 0.6738 0.7176
-0.750 0.1931 0.01114 0.00568 -0.0538 0.6703 0.7190
-0.500 0.2212 0.01108 0.00558 -0.0542 0.6667 0.7203
-0.250 0.2490 0.01101 0.00549 -0.0546 0.6629 0.7218
0.000 0.2772 0.01096 0.00539 -0.0550 0.6592 0.7233
0.250 0.3058 0.01093 0.00529 -0.0556 0.6558 0.7244
0.500 0.3346 0.01090 0.00520 -0.0561 0.6525 0.7253
0.750 0.3617 0.01081 0.00514 -0.0562 0.6489 0.7262
1.000 0.3894 0.01077 0.00511 -0.0564 0.6450 0.7271
1.250 0.4174 0.01076 0.00509 -0.0567 0.6413 0.7282
1.500 0.4463 0.01080 0.00508 -0.0572 0.6375 0.7292
1.750 0.4732 0.01077 0.00508 -0.0573 0.6332 0.7301
2.000 0.5006 0.01074 0.00506 -0.0574 0.6288 0.7311
2.250 0.5286 0.01074 0.00504 -0.0577 0.6248 0.7322
2.500 0.5574 0.01079 0.00506 -0.0582 0.6209 0.7332
2.750 0.5840 0.01075 0.00507 -0.0583 0.6164 0.7344
3.000 0.6113 0.01073 0.00506 -0.0584 0.6116 0.7355
3.250 0.6394 0.01075 0.00506 -0.0588 0.6071 0.7369
3.500 0.6666 0.01078 0.00510 -0.0589 0.6025 0.7382
3.750 0.6934 0.01077 0.00512 -0.0590 0.5974 0.7394
4.000 0.7209 0.01078 0.00513 -0.0592 0.5924 0.7404
4.250 0.7478 0.01078 0.00514 -0.0593 0.5872 0.7414
4.500 0.7733 0.01074 0.00516 -0.0591 0.5811 0.7424
4.750 0.8000 0.01076 0.00518 -0.0591 0.5753 0.7434
5.000 0.8253 0.01076 0.00526 -0.0589 0.5690 0.7445
5.250 0.8507 0.01077 0.00531 -0.0586 0.5622 0.7455
5.500 0.8760 0.01081 0.00538 -0.0583 0.5552 0.7467
5.750 0.9005 0.01082 0.00545 -0.0579 0.5470 0.7479
6.000 0.9247 0.01087 0.00553 -0.0574 0.5383 0.7494
6.250 0.9482 0.01093 0.00561 -0.0568 0.5283 0.7509
6.500 0.9714 0.01098 0.00571 -0.0562 0.5170 0.7525
6.750 0.9937 0.01106 0.00582 -0.0554 0.5045 0.7539
7.000 1.0145 0.01117 0.00593 -0.0543 0.4886 0.7552
7.250 1.0333 0.01135 0.00608 -0.0528 0.4694 0.7564
7.500 1.0487 0.01155 0.00624 -0.0507 0.4455 0.7578
7.750 1.0582 0.01188 0.00648 -0.0475 0.4170 0.7593
8.000 1.0635 0.01230 0.00681 -0.0435 0.3878 0.7608
8.250 1.0687 0.01287 0.00726 -0.0397 0.3583 0.7624
8.500 1.0741 0.01352 0.00780 -0.0362 0.3295 0.7641
8.750 1.0789 0.01423 0.00841 -0.0327 0.3019 0.7661
9.000 1.0831 0.01500 0.00908 -0.0292 0.2760 0.7682
9.250 1.0866 0.01586 0.00983 -0.0259 0.2507 0.7703
9.500 1.0920 0.01672 0.01061 -0.0231 0.2287 0.7721
9.750 1.0964 0.01763 0.01146 -0.0203 0.2080 0.7739
10.000 1.1001 0.01865 0.01242 -0.0175 0.1883 0.7758
10.250 1.1052 0.01968 0.01341 -0.0152 0.1701 0.7777
10.500 1.1100 0.02080 0.01449 -0.0129 0.1531 0.7798
10.750 1.1142 0.02203 0.01566 -0.0108 0.1363 0.7820
11.000 1.1185 0.02332 0.01691 -0.0088 0.1212 0.7843
11.250 1.1227 0.02469 0.01822 -0.0070 0.1067 0.7865
11.500 1.1279 0.02605 0.01954 -0.0054 0.0944 0.7887
11.750 1.1325 0.02744 0.02093 -0.0038 0.0828 0.7911
12.000 1.1376 0.02888 0.02238 -0.0023 0.0729 0.7936
12.250 1.1423 0.03040 0.02390 -0.0010 0.0642 0.7964
12.500 1.1460 0.03206 0.02554 0.0003 0.0561 0.7993
12.750 1.1508 0.03371 0.02720 0.0014 0.0494 0.8022
13.000 1.1563 0.03534 0.02886 0.0023 0.0437 0.8049
13.250 1.1591 0.03720 0.03075 0.0034 0.0388 0.8079
13.500 1.1647 0.03891 0.03252 0.0041 0.0348 0.8111
13.750 1.1685 0.04084 0.03449 0.0049 0.0312 0.8146
14.000 1.1730 0.04278 0.03647 0.0054 0.0282 0.8183
14.250 1.1762 0.04487 0.03863 0.0060 0.0255 0.8220
14.500 1.1804 0.04691 0.04076 0.0064 0.0232 0.8262
14.750 1.1816 0.04932 0.04323 0.0068 0.0212 0.8309
15.000 1.1864 0.05146 0.04547 0.0069 0.0194 0.8360
15.250 1.1847 0.05426 0.04834 0.0071 0.0176 0.8416
15.500 1.1912 0.05629 0.05049 0.0071 0.0160 0.8490
15.750 1.1901 0.05917 0.05346 0.0071 0.0145 0.8575
16.000 1.1907 0.06188 0.05631 0.0071 0.0134 0.8690
16.250 1.1898 0.06459 0.05921 0.0073 0.0125 0.8894
16.500 1.1953 0.06800 0.06283 0.0051 0.0117 0.9444
16.750 1.1903 0.07167 0.06659 0.0044 0.0106 1.0000
17.000 1.1905 0.07502 0.07004 0.0034 0.0098 1.0000
17.250 1.1891 0.07863 0.07371 0.0023 0.0092 1.0000
17.500 1.1793 0.08351 0.07867 0.0008 0.0086 1.0000
17.750 1.1803 0.08696 0.08223 -0.0004 0.0082 1.0000
18.000 1.1759 0.09125 0.08663 -0.0020 0.0078 1.0000
18.250 1.1721 0.09556 0.09103 -0.0037 0.0075 1.0000
18.500 1.1672 0.10011 0.09567 -0.0056 0.0070 1.0000
18.750 1.1593 0.10523 0.10087 -0.0078 0.0067 1.0000
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Polar data table (+)
Polar graphs
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