EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 500,000 Max Cl/Cd: 96.04 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e549-il-500000.txt Download as CSV file: xf-e549-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 549 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3161 0.10827 0.10619 -0.0567 1.0000 0.0230
-13.250 -0.3263 0.10246 0.10039 -0.0587 1.0000 0.0232
-13.000 -0.6869 0.05557 0.05189 -0.0778 1.0000 0.0107
-12.750 -0.6801 0.05347 0.04981 -0.0771 1.0000 0.0103
-12.500 -0.6957 0.04976 0.04597 -0.0764 1.0000 0.0101
-12.250 -0.7122 0.04617 0.04221 -0.0752 1.0000 0.0099
-12.000 -0.7211 0.04367 0.03959 -0.0737 1.0000 0.0097
-11.750 -0.7349 0.04073 0.03646 -0.0714 1.0000 0.0095
-11.500 -0.7498 0.03808 0.03361 -0.0681 1.0000 0.0093
-11.250 -0.7414 0.03381 0.02888 -0.0689 0.9972 0.0088
-11.000 -0.7175 0.03104 0.02579 -0.0705 0.9927 0.0085
-10.750 -0.6912 0.02919 0.02377 -0.0721 0.9855 0.0085
-10.500 -0.6667 0.02767 0.02215 -0.0732 0.9733 0.0087
-10.250 -0.6386 0.02627 0.02064 -0.0747 0.9630 0.0087
-10.000 -0.6051 0.02491 0.01920 -0.0774 0.9551 0.0090
-9.750 -0.5664 0.02356 0.01776 -0.0812 0.9472 0.0094
-9.500 -0.5235 0.02223 0.01633 -0.0859 0.9386 0.0099
-9.250 -0.4804 0.02092 0.01491 -0.0909 0.9257 0.0103
-9.000 -0.4512 0.01952 0.01338 -0.0937 0.9045 0.0110
-8.750 -0.4330 0.01860 0.01235 -0.0938 0.8834 0.0118
-8.500 -0.4201 0.01784 0.01146 -0.0926 0.8654 0.0125
-8.250 -0.4082 0.01720 0.01070 -0.0909 0.8499 0.0135
-8.000 -0.4053 0.01627 0.00967 -0.0880 0.8350 0.0142
-7.750 -0.4015 0.01562 0.00895 -0.0848 0.8220 0.0153
-7.500 -0.3917 0.01517 0.00841 -0.0823 0.8109 0.0168
-7.250 -0.3792 0.01465 0.00783 -0.0802 0.8010 0.0203
-7.000 -0.3660 0.01409 0.00723 -0.0782 0.7907 0.0262
-6.750 -0.3524 0.01346 0.00663 -0.0763 0.7817 0.0394
-6.500 -0.3364 0.01288 0.00613 -0.0748 0.7729 0.0616
-6.250 -0.3198 0.01227 0.00567 -0.0735 0.7647 0.0954
-6.000 -0.3031 0.01159 0.00518 -0.0722 0.7566 0.1466
-5.750 -0.2888 0.01061 0.00457 -0.0709 0.7485 0.2358
-5.500 -0.2793 0.00904 0.00371 -0.0691 0.7407 0.4041
-5.250 -0.2572 0.00871 0.00371 -0.0683 0.7332 0.5109
-5.000 -0.2297 0.00883 0.00376 -0.0682 0.7261 0.5366
-4.750 -0.2018 0.00899 0.00383 -0.0681 0.7192 0.5523
-4.500 -0.1740 0.00912 0.00390 -0.0681 0.7119 0.5618
-4.250 -0.1459 0.00925 0.00389 -0.0681 0.7052 0.5701
-4.000 -0.1179 0.00938 0.00402 -0.0680 0.6979 0.5773
-3.750 -0.0898 0.00956 0.00404 -0.0681 0.6918 0.5846
-3.500 -0.0618 0.00970 0.00423 -0.0679 0.6848 0.5917
-3.250 -0.0340 0.01001 0.00445 -0.0677 0.6783 0.6023
-3.000 -0.0060 0.01023 0.00470 -0.0676 0.6718 0.6086
-2.750 0.0222 0.01022 0.00462 -0.0677 0.6652 0.6112
-2.500 0.0504 0.01021 0.00450 -0.0679 0.6594 0.6132
-2.250 0.0786 0.01017 0.00439 -0.0682 0.6528 0.6151
-2.000 0.1069 0.01017 0.00427 -0.0685 0.6470 0.6165
-1.750 0.1350 0.01008 0.00415 -0.0687 0.6411 0.6180
-1.500 0.1630 0.01003 0.00407 -0.0688 0.6348 0.6195
-1.250 0.1912 0.01004 0.00400 -0.0690 0.6292 0.6208
-1.000 0.2192 0.01000 0.00395 -0.0692 0.6229 0.6221
-0.750 0.2473 0.01000 0.00390 -0.0694 0.6172 0.6235
-0.500 0.2755 0.01002 0.00387 -0.0696 0.6119 0.6252
-0.250 0.3036 0.01001 0.00384 -0.0698 0.6061 0.6270
0.000 0.3318 0.01004 0.00379 -0.0701 0.6010 0.6286
0.250 0.3601 0.01005 0.00377 -0.0703 0.5960 0.6301
0.500 0.3882 0.01006 0.00375 -0.0706 0.5907 0.6316
0.750 0.4164 0.01009 0.00371 -0.0708 0.5859 0.6329
1.000 0.4444 0.01008 0.00370 -0.0710 0.5813 0.6344
1.250 0.4723 0.01007 0.00373 -0.0712 0.5765 0.6359
1.500 0.5001 0.01011 0.00375 -0.0714 0.5719 0.6376
1.750 0.5283 0.01019 0.00380 -0.0716 0.5676 0.6393
2.000 0.5560 0.01020 0.00384 -0.0718 0.5628 0.6410
2.250 0.5838 0.01024 0.00388 -0.0719 0.5583 0.6427
2.500 0.6119 0.01032 0.00392 -0.0722 0.5542 0.6445
2.750 0.6397 0.01038 0.00398 -0.0724 0.5498 0.6463
3.000 0.6673 0.01042 0.00404 -0.0725 0.5450 0.6479
3.250 0.6949 0.01046 0.00408 -0.0727 0.5408 0.6497
3.500 0.7228 0.01055 0.00416 -0.0729 0.5369 0.6515
3.750 0.7499 0.01058 0.00427 -0.0729 0.5328 0.6535
4.000 0.7772 0.01064 0.00438 -0.0730 0.5286 0.6556
4.250 0.8045 0.01073 0.00446 -0.0731 0.5243 0.6578
4.500 0.8313 0.01082 0.00457 -0.0731 0.5191 0.6600
4.750 0.8574 0.01085 0.00465 -0.0730 0.5128 0.6621
5.000 0.8842 0.01098 0.00473 -0.0730 0.5076 0.6642
5.250 0.9101 0.01100 0.00485 -0.0728 0.5021 0.6664
5.500 0.9357 0.01105 0.00495 -0.0726 0.4960 0.6686
5.750 0.9614 0.01117 0.00508 -0.0724 0.4901 0.6709
6.000 0.9866 0.01122 0.00522 -0.0721 0.4839 0.6737
6.250 1.0117 0.01134 0.00535 -0.0717 0.4776 0.6766
6.500 1.0367 0.01144 0.00550 -0.0714 0.4710 0.6795
6.750 1.0606 0.01152 0.00563 -0.0709 0.4636 0.6822
7.000 1.0843 0.01161 0.00580 -0.0703 0.4557 0.6850
7.250 1.1069 0.01175 0.00596 -0.0695 0.4471 0.6881
7.500 1.1299 0.01186 0.00615 -0.0688 0.4378 0.6914
7.750 1.1512 0.01204 0.00633 -0.0678 0.4276 0.6948
8.000 1.1710 0.01221 0.00654 -0.0666 0.4158 0.6982
8.250 1.1899 0.01239 0.00678 -0.0652 0.4020 0.7017
8.500 1.2050 0.01264 0.00703 -0.0630 0.3861 0.7057
8.750 1.2174 0.01296 0.00732 -0.0604 0.3676 0.7102
9.000 1.2281 0.01337 0.00771 -0.0576 0.3459 0.7145
9.250 1.2345 0.01396 0.00825 -0.0543 0.3186 0.7194
9.500 1.2374 0.01475 0.00891 -0.0505 0.2936 0.7249
9.750 1.2418 0.01553 0.00965 -0.0472 0.2766 0.7302
10.000 1.2475 0.01632 0.01043 -0.0442 0.2617 0.7363
10.250 1.2548 0.01711 0.01122 -0.0417 0.2465 0.7431
10.500 1.2613 0.01795 0.01208 -0.0391 0.2273 0.7502
10.750 1.2629 0.01910 0.01316 -0.0362 0.2063 0.7588
11.000 1.2638 0.02035 0.01440 -0.0334 0.1883 0.7683
11.250 1.2649 0.02168 0.01574 -0.0309 0.1727 0.7795
11.500 1.2654 0.02312 0.01719 -0.0285 0.1575 0.7936
11.750 1.2656 0.02462 0.01874 -0.0262 0.1435 0.8128
12.000 1.2650 0.02617 0.02036 -0.0239 0.1307 0.8427
12.250 1.2699 0.02768 0.02210 -0.0230 0.1181 1.0000
12.500 1.2712 0.02961 0.02398 -0.0217 0.1064 1.0000
12.750 1.2719 0.03165 0.02597 -0.0205 0.0962 1.0000
13.000 1.2740 0.03364 0.02796 -0.0195 0.0866 1.0000
13.250 1.2761 0.03570 0.03002 -0.0187 0.0784 1.0000
13.500 1.2764 0.03799 0.03230 -0.0178 0.0710 1.0000
13.750 1.2784 0.04020 0.03452 -0.0172 0.0643 1.0000
14.000 1.2797 0.04255 0.03688 -0.0167 0.0581 1.0000
14.250 1.2801 0.04505 0.03938 -0.0163 0.0528 1.0000
14.500 1.2818 0.04750 0.04186 -0.0160 0.0476 1.0000
14.750 1.2811 0.05026 0.04462 -0.0158 0.0430 1.0000
15.000 1.2828 0.05284 0.04725 -0.0157 0.0392 1.0000
15.250 1.2833 0.05561 0.05004 -0.0158 0.0358 1.0000
15.500 1.2817 0.05871 0.05317 -0.0159 0.0326 1.0000
15.750 1.2844 0.06136 0.05590 -0.0162 0.0300 1.0000
16.000 1.2814 0.06473 0.05928 -0.0166 0.0273 1.0000
16.250 1.2820 0.06778 0.06241 -0.0170 0.0254 1.0000
16.500 1.2834 0.07077 0.06545 -0.0176 0.0233 1.0000
16.750 1.2793 0.07452 0.06923 -0.0183 0.0214 1.0000
17.000 1.2793 0.07783 0.07264 -0.0191 0.0200 1.0000
17.250 1.2793 0.08120 0.07607 -0.0200 0.0186 1.0000
17.500 1.2756 0.08513 0.08005 -0.0211 0.0173 1.0000
17.750 1.2706 0.08934 0.08434 -0.0223 0.0163 1.0000
18.000 1.2709 0.09284 0.08794 -0.0235 0.0153 1.0000
18.250 1.2689 0.09673 0.09190 -0.0249 0.0142 1.0000
18.500 1.2637 0.10117 0.09642 -0.0265 0.0136 1.0000
18.750 1.2570 0.10593 0.10126 -0.0283 0.0127 1.0000
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Polar data table (+)
Polar graphs
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