EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 200,000 Max Cl/Cd: 66.08 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e549-il-200000-n5.txt Download as CSV file: xf-e549-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5616 0.09348 0.08934 -0.0617 1.0000 0.0084
-14.500 -0.6077 0.08059 0.07610 -0.0690 1.0000 0.0083
-14.250 -0.6325 0.07330 0.06857 -0.0724 1.0000 0.0082
-14.000 -0.6525 0.06747 0.06251 -0.0746 1.0000 0.0081
-13.750 -0.6673 0.06283 0.05767 -0.0758 1.0000 0.0081
-13.500 -0.6774 0.05924 0.05397 -0.0764 1.0000 0.0082
-13.250 -0.6860 0.05593 0.05051 -0.0766 1.0000 0.0083
-13.000 -0.6943 0.05265 0.04702 -0.0763 1.0000 0.0082
-12.750 -0.6996 0.04993 0.04417 -0.0758 1.0000 0.0083
-12.500 -0.7026 0.04762 0.04174 -0.0751 1.0000 0.0084
-12.250 -0.7046 0.04548 0.03950 -0.0741 1.0000 0.0086
-12.000 -0.7050 0.04340 0.03726 -0.0728 1.0000 0.0086
-11.750 -0.7047 0.04157 0.03532 -0.0713 1.0000 0.0087
-11.500 -0.7039 0.03998 0.03364 -0.0696 1.0000 0.0089
-11.250 -0.7028 0.03849 0.03205 -0.0676 1.0000 0.0090
-11.000 -0.6877 0.03671 0.03012 -0.0680 0.9965 0.0092
-10.500 -0.6430 0.03326 0.02637 -0.0705 0.9715 0.0099
-10.250 -0.6174 0.03179 0.02476 -0.0721 0.9597 0.0102
-10.000 -0.5894 0.03031 0.02319 -0.0746 0.9490 0.0110
-9.750 -0.5573 0.02899 0.02181 -0.0777 0.9393 0.0121
-9.500 -0.5243 0.02766 0.02033 -0.0807 0.9283 0.0132
-9.250 -0.4942 0.02618 0.01875 -0.0834 0.9153 0.0139
-9.000 -0.4647 0.02489 0.01737 -0.0861 0.9009 0.0148
-8.750 -0.4396 0.02371 0.01608 -0.0877 0.8855 0.0161
-8.500 -0.4197 0.02262 0.01485 -0.0882 0.8701 0.0177
-8.250 -0.4027 0.02173 0.01388 -0.0880 0.8556 0.0198
-8.000 -0.3890 0.02089 0.01296 -0.0870 0.8418 0.0227
-7.750 -0.3780 0.02008 0.01206 -0.0854 0.8291 0.0263
-7.500 -0.3708 0.01932 0.01123 -0.0831 0.8173 0.0301
-7.250 -0.3638 0.01870 0.01058 -0.0805 0.8056 0.0364
-7.000 -0.3529 0.01806 0.00992 -0.0784 0.7955 0.0468
-6.750 -0.3401 0.01744 0.00930 -0.0766 0.7862 0.0626
-6.500 -0.3279 0.01678 0.00872 -0.0748 0.7766 0.0859
-6.250 -0.3149 0.01605 0.00811 -0.0731 0.7684 0.1213
-6.000 -0.3033 0.01518 0.00748 -0.0713 0.7595 0.1764
-5.750 -0.2952 0.01394 0.00667 -0.0693 0.7517 0.2753
-5.500 -0.2882 0.01274 0.00633 -0.0667 0.7435 0.4422
-5.250 -0.2632 0.01287 0.00652 -0.0660 0.7364 0.5095
-5.000 -0.2368 0.01302 0.00658 -0.0656 0.7288 0.5336
-4.750 -0.2096 0.01318 0.00657 -0.0654 0.7226 0.5506
-4.500 -0.1829 0.01337 0.00669 -0.0651 0.7151 0.5631
-4.250 -0.1556 0.01366 0.00686 -0.0647 0.7086 0.5762
-4.000 -0.1288 0.01409 0.00725 -0.0641 0.7014 0.5906
-3.750 -0.1020 0.01434 0.00737 -0.0637 0.6949 0.6019
-3.500 -0.0743 0.01439 0.00734 -0.0636 0.6889 0.6047
-3.250 -0.0470 0.01433 0.00719 -0.0636 0.6822 0.6069
-3.000 -0.0194 0.01427 0.00698 -0.0637 0.6765 0.6091
-2.750 0.0077 0.01418 0.00680 -0.0638 0.6697 0.6115
-2.500 0.0351 0.01409 0.00657 -0.0640 0.6637 0.6138
-2.250 0.0627 0.01399 0.00632 -0.0642 0.6581 0.6165
-2.000 0.0901 0.01394 0.00622 -0.0643 0.6518 0.6179
-1.750 0.1178 0.01390 0.00609 -0.0644 0.6464 0.6191
-1.500 0.1452 0.01387 0.00601 -0.0645 0.6405 0.6206
-1.250 0.1727 0.01385 0.00593 -0.0646 0.6348 0.6223
-1.000 0.2006 0.01385 0.00583 -0.0647 0.6300 0.6242
-0.750 0.2278 0.01382 0.00577 -0.0649 0.6240 0.6260
-0.500 0.2554 0.01379 0.00568 -0.0650 0.6186 0.6278
-0.250 0.2835 0.01379 0.00557 -0.0653 0.6143 0.6297
0.000 0.3109 0.01377 0.00552 -0.0655 0.6087 0.6317
0.250 0.3383 0.01378 0.00549 -0.0656 0.6036 0.6334
0.500 0.3661 0.01381 0.00548 -0.0658 0.5993 0.6349
0.750 0.3931 0.01383 0.00552 -0.0658 0.5941 0.6365
1.000 0.4203 0.01386 0.00554 -0.0659 0.5889 0.6381
1.250 0.4480 0.01390 0.00553 -0.0660 0.5843 0.6398
1.500 0.4749 0.01393 0.00557 -0.0661 0.5788 0.6417
1.750 0.5020 0.01397 0.00559 -0.0661 0.5732 0.6436
2.000 0.5297 0.01402 0.00559 -0.0663 0.5687 0.6457
2.250 0.5568 0.01408 0.00566 -0.0665 0.5638 0.6481
2.500 0.5835 0.01414 0.00575 -0.0665 0.5592 0.6499
2.750 0.6107 0.01421 0.00585 -0.0665 0.5553 0.6516
3.000 0.6381 0.01430 0.00594 -0.0666 0.5517 0.6534
3.250 0.6644 0.01438 0.00609 -0.0666 0.5469 0.6554
3.500 0.6909 0.01446 0.00620 -0.0666 0.5420 0.6575
3.750 0.7183 0.01456 0.00627 -0.0667 0.5375 0.6598
4.250 0.7705 0.01476 0.00658 -0.0666 0.5276 0.6646
4.500 0.7971 0.01487 0.00673 -0.0665 0.5239 0.6666
4.750 0.8231 0.01499 0.00693 -0.0664 0.5195 0.6690
5.000 0.8481 0.01510 0.00714 -0.0661 0.5141 0.6716
5.250 0.8742 0.01523 0.00731 -0.0660 0.5094 0.6743
5.500 0.8997 0.01536 0.00749 -0.0658 0.5042 0.6771
5.750 0.9237 0.01548 0.00768 -0.0654 0.4969 0.6800
6.000 0.9483 0.01559 0.00782 -0.0650 0.4905 0.6823
6.250 0.9708 0.01571 0.00808 -0.0642 0.4827 0.6849
6.500 0.9949 0.01585 0.00825 -0.0637 0.4762 0.6879
6.750 1.0168 0.01600 0.00852 -0.0629 0.4678 0.6912
7.000 1.0395 0.01616 0.00870 -0.0622 0.4600 0.6950
7.250 1.0601 0.01632 0.00900 -0.0611 0.4509 0.6982
7.500 1.0804 0.01650 0.00926 -0.0600 0.4420 0.7017
7.750 1.0994 0.01669 0.00952 -0.0586 0.4316 0.7058
8.000 1.1172 0.01692 0.00983 -0.0571 0.4198 0.7100
8.250 1.1332 0.01715 0.01015 -0.0552 0.4070 0.7138
8.500 1.1452 0.01741 0.01047 -0.0527 0.3929 0.7179
8.750 1.1559 0.01775 0.01085 -0.0500 0.3775 0.7227
9.000 1.1650 0.01822 0.01132 -0.0471 0.3596 0.7278
9.250 1.1713 0.01880 0.01190 -0.0440 0.3403 0.7328
9.500 1.1765 0.01950 0.01259 -0.0409 0.3177 0.7390
10.000 1.1766 0.02153 0.01453 -0.0341 0.2809 0.7526
10.500 1.1808 0.02388 0.01691 -0.0288 0.2519 0.7691
10.750 1.1851 0.02509 0.01818 -0.0268 0.2357 0.7786
11.250 1.1875 0.02809 0.02122 -0.0227 0.1998 0.8034
11.750 1.1854 0.03163 0.02486 -0.0189 0.1708 0.8449
12.000 1.1861 0.03341 0.02680 -0.0175 0.1573 0.9072
12.250 1.1855 0.03535 0.02875 -0.0164 0.1452 1.0000
12.500 1.1858 0.03757 0.03094 -0.0155 0.1333 1.0000
12.750 1.1856 0.03991 0.03326 -0.0148 0.1226 1.0000
13.000 1.1875 0.04214 0.03550 -0.0143 0.1124 1.0000
13.250 1.1889 0.04449 0.03786 -0.0139 0.1031 1.0000
13.500 1.1890 0.04705 0.04041 -0.0135 0.0946 1.0000
13.750 1.1903 0.04955 0.04293 -0.0133 0.0865 1.0000
14.000 1.1919 0.05209 0.04552 -0.0132 0.0796 1.0000
14.250 1.1914 0.05493 0.04836 -0.0132 0.0728 1.0000
14.500 1.1939 0.05752 0.05100 -0.0133 0.0666 1.0000
14.750 1.1928 0.06056 0.05405 -0.0135 0.0613 1.0000
15.000 1.1951 0.06328 0.05684 -0.0138 0.0561 1.0000
15.250 1.1943 0.06644 0.06003 -0.0142 0.0516 1.0000
15.500 1.1954 0.06943 0.06309 -0.0147 0.0475 1.0000
15.750 1.1954 0.07263 0.06634 -0.0153 0.0437 1.0000
16.000 1.1934 0.07614 0.06990 -0.0161 0.0407 1.0000
16.250 1.1945 0.07931 0.07318 -0.0168 0.0377 1.0000
16.500 1.1931 0.08290 0.07682 -0.0178 0.0349 1.0000
16.750 1.1900 0.08679 0.08078 -0.0189 0.0329 1.0000
17.000 1.1901 0.09027 0.08439 -0.0199 0.0306 1.0000
17.250 1.1883 0.09409 0.08828 -0.0212 0.0285 1.0000
17.500 1.1836 0.09843 0.09268 -0.0227 0.0270 1.0000
17.750 1.1816 0.10241 0.09676 -0.0242 0.0255 1.0000
18.000 1.1800 0.10637 0.10084 -0.0258 0.0239 1.0000
18.250 1.1764 0.11071 0.10527 -0.0276 0.0224 1.0000
18.500 1.1709 0.11543 0.11005 -0.0297 0.0214 1.0000
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Polar data table (+)
Polar graphs
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