EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 100,000 Max Cl/Cd: 43.25 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e549-il-100000.txt Download as CSV file: xf-e549-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3291 0.09669 0.09231 -0.0616 1.0000 0.0710
-11.750 -0.4235 0.07791 0.07343 -0.0725 1.0000 0.0637
-11.500 -0.4469 0.07231 0.06776 -0.0732 1.0000 0.0601
-11.250 -0.5072 0.07820 0.07340 -0.0727 1.0000 0.0684
-11.000 -0.5459 0.07301 0.06815 -0.0734 1.0000 0.0669
-10.750 -0.5878 0.06934 0.06441 -0.0719 1.0000 0.0657
-10.500 -0.6274 0.06749 0.06253 -0.0678 1.0000 0.0651
-10.250 -0.6538 0.06717 0.06229 -0.0625 1.0000 0.0658
-10.000 -0.6817 0.06729 0.06250 -0.0567 1.0000 0.0668
-9.750 -0.7150 0.06735 0.06259 -0.0504 1.0000 0.0676
-9.500 -0.7553 0.06375 0.05856 -0.0459 0.9973 0.0594
-9.250 -0.7594 0.05675 0.05054 -0.0475 0.9857 0.0504
-9.000 -0.7388 0.05166 0.04519 -0.0496 0.9787 0.0488
-8.750 -0.7158 0.04727 0.04035 -0.0516 0.9716 0.0473
-8.500 -0.6940 0.04370 0.03631 -0.0523 0.9631 0.0465
-8.250 -0.6590 0.04029 0.03243 -0.0545 0.9577 0.0466
-8.000 -0.6305 0.03801 0.02984 -0.0551 0.9493 0.0478
-7.750 -0.5909 0.03625 0.02761 -0.0576 0.9437 0.0511
-7.500 -0.5519 0.03372 0.02525 -0.0594 0.9385 0.0555
-7.250 -0.5121 0.03216 0.02356 -0.0610 0.9323 0.0613
-7.000 -0.4680 0.03039 0.02190 -0.0637 0.9285 0.0740
-6.750 -0.4479 0.02897 0.02074 -0.0628 0.9191 0.0895
-6.500 -0.4227 0.02702 0.01914 -0.0636 0.9127 0.1277
-6.250 -0.4274 0.02507 0.01778 -0.0603 0.9001 0.1905
-6.000 -0.4418 0.02359 0.01844 -0.0541 0.8881 0.4903
-5.750 -0.3970 0.02668 0.02121 -0.0534 0.8825 0.5854
-5.500 -0.3305 0.03098 0.02536 -0.0527 0.8807 0.6150
-5.250 -0.2558 0.03464 0.02881 -0.0531 0.8791 0.6348
-5.000 -0.1494 0.03761 0.03146 -0.0583 0.8808 0.6536
-4.750 -0.0583 0.03854 0.03208 -0.0650 0.8802 0.6760
-4.500 -0.0184 0.03868 0.03207 -0.0659 0.8712 0.6906
-4.250 0.0342 0.03817 0.03136 -0.0696 0.8662 0.7041
-4.000 0.0510 0.03788 0.03097 -0.0681 0.8555 0.7153
-3.750 0.0745 0.03728 0.03023 -0.0683 0.8484 0.7257
-3.500 0.1128 0.03697 0.02981 -0.0696 0.8390 0.7347
-3.250 0.1130 0.03655 0.02931 -0.0664 0.8298 0.7409
-3.000 0.1505 0.03607 0.02872 -0.0681 0.8217 0.7485
-2.750 0.1644 0.03564 0.02820 -0.0667 0.8136 0.7532
-2.500 0.1548 0.03531 0.02784 -0.0618 0.8039 0.7564
-2.250 0.1442 0.03515 0.02765 -0.0565 0.7941 0.7595
-2.000 0.1960 0.03452 0.02690 -0.0607 0.7887 0.7643
-1.750 0.1934 0.03437 0.02673 -0.0566 0.7800 0.7668
-1.500 0.1879 0.03404 0.02636 -0.0522 0.7725 0.7690
-1.250 0.1605 0.03403 0.02636 -0.0447 0.7627 0.7712
-1.000 0.1542 0.03343 0.02570 -0.0410 0.7563 0.7738
-0.750 0.1611 0.03349 0.02575 -0.0381 0.7478 0.7760
-0.500 0.1842 0.03313 0.02534 -0.0380 0.7423 0.7782
-0.250 0.2155 0.03259 0.02470 -0.0392 0.7389 0.7803
0.000 0.1892 0.03303 0.02520 -0.0323 0.7280 0.7830
0.250 0.2193 0.03243 0.02450 -0.0336 0.7245 0.7850
0.500 0.1964 0.03298 0.02509 -0.0280 0.7138 0.7881
0.750 0.2263 0.03259 0.02463 -0.0292 0.7101 0.7902
1.000 0.2655 0.03212 0.02410 -0.0313 0.7078 0.7917
1.250 0.2391 0.03337 0.02543 -0.0250 0.6963 0.7942
1.500 0.2784 0.03290 0.02491 -0.0270 0.6936 0.7966
1.750 0.2538 0.03443 0.02649 -0.0218 0.6826 0.7998
2.000 0.2879 0.03424 0.02626 -0.0237 0.6794 0.8019
2.250 0.3314 0.03378 0.02576 -0.0268 0.6773 0.8040
2.500 0.2944 0.03595 0.02800 -0.0200 0.6648 0.8071
2.750 0.3463 0.03511 0.02714 -0.0230 0.6627 0.8094
3.000 0.4002 0.03412 0.02613 -0.0264 0.6611 0.8118
3.250 0.3618 0.03665 0.02873 -0.0201 0.6479 0.8152
3.500 0.3960 0.03654 0.02862 -0.0216 0.6433 0.8179
3.750 0.3912 0.03807 0.03016 -0.0194 0.6331 0.8211
4.000 0.3779 0.04034 0.03248 -0.0164 0.6233 0.8247
4.250 0.4022 0.04067 0.03285 -0.0166 0.6184 0.8282
4.500 0.4491 0.03979 0.03201 -0.0186 0.6162 0.8316
4.750 0.5054 0.03843 0.03068 -0.0217 0.6150 0.8346
5.250 0.4557 0.04482 0.03717 -0.0150 0.5904 0.8428
5.500 0.4915 0.04457 0.03699 -0.0160 0.5865 0.8473
5.750 0.4900 0.04660 0.03907 -0.0148 0.5767 0.8523
6.000 0.5215 0.04630 0.03885 -0.0149 0.5716 0.8571
6.250 0.5711 0.04501 0.03765 -0.0164 0.5693 0.8622
6.500 0.6272 0.04320 0.03593 -0.0183 0.5681 0.8670
6.750 0.5836 0.04782 0.04060 -0.0142 0.5490 0.8737
7.000 0.6697 0.04352 0.03643 -0.0171 0.5523 0.8795
7.250 0.6370 0.04751 0.04049 -0.0138 0.5339 0.8879
7.500 0.7130 0.04354 0.03666 -0.0157 0.5363 0.8960
7.750 0.7837 0.03991 0.03320 -0.0175 0.5368 0.9038
8.000 0.7553 0.04341 0.03680 -0.0139 0.5202 0.9181
8.250 0.8334 0.03922 0.03279 -0.0163 0.5206 0.9288
8.500 0.8515 0.03972 0.03346 -0.0163 0.5093 0.9490
8.750 0.9623 0.03447 0.02839 -0.0230 0.5084 0.9583
9.000 0.9877 0.03470 0.02878 -0.0242 0.4960 1.0000
9.250 1.0604 0.03220 0.02638 -0.0291 0.4873 1.0000
9.500 1.1429 0.02945 0.02363 -0.0355 0.4760 1.0000
9.750 1.1663 0.02923 0.02349 -0.0356 0.4618 1.0000
10.000 1.1901 0.02894 0.02326 -0.0355 0.4470 1.0000
10.250 1.2124 0.02862 0.02296 -0.0349 0.4315 1.0000
10.500 1.2305 0.02845 0.02277 -0.0336 0.4152 1.0000
10.750 1.2323 0.02896 0.02332 -0.0306 0.3987 1.0000
11.000 1.2326 0.02967 0.02405 -0.0276 0.3812 1.0000
11.250 1.2338 0.03048 0.02485 -0.0249 0.3625 1.0000
11.500 1.2368 0.03133 0.02565 -0.0225 0.3427 1.0000
11.750 1.2347 0.03266 0.02690 -0.0200 0.3224 1.0000
12.000 1.2316 0.03424 0.02840 -0.0177 0.3017 1.0000
12.250 1.2349 0.03565 0.02956 -0.0159 0.2805 1.0000
12.500 1.2310 0.03774 0.03158 -0.0140 0.2603 1.0000
12.750 1.2265 0.03998 0.03376 -0.0123 0.2413 1.0000
13.000 1.2206 0.04237 0.03609 -0.0109 0.2240 1.0000
13.250 1.2163 0.04474 0.03833 -0.0097 0.2076 1.0000
13.500 1.2118 0.04732 0.04081 -0.0086 0.1917 1.0000
13.750 1.2079 0.04998 0.04340 -0.0078 0.1765 1.0000
14.000 1.2056 0.05264 0.04601 -0.0071 0.1621 1.0000
14.250 1.2047 0.05527 0.04854 -0.0065 0.1489 1.0000
14.500 1.2042 0.05792 0.05113 -0.0061 0.1368 1.0000
14.750 1.2005 0.06105 0.05435 -0.0059 0.1263 1.0000
15.000 1.2008 0.06389 0.05720 -0.0057 0.1163 1.0000
15.250 1.2048 0.06639 0.05963 -0.0054 0.1069 1.0000
15.500 1.2042 0.06938 0.06264 -0.0055 0.0988 1.0000
15.750 1.2050 0.07246 0.06581 -0.0056 0.0916 1.0000
16.000 1.2162 0.07436 0.06751 -0.0053 0.0835 1.0000
16.250 1.2075 0.07856 0.07204 -0.0060 0.0792 1.0000
16.500 1.2162 0.08072 0.07408 -0.0060 0.0731 1.0000
16.750 1.2122 0.08471 0.07833 -0.0066 0.0692 1.0000
17.000 1.2063 0.08883 0.08265 -0.0075 0.0655 1.0000
17.250 1.2213 0.09063 0.08428 -0.0072 0.0603 1.0000
17.500 1.2067 0.09595 0.08994 -0.0089 0.0586 1.0000
17.750 1.1946 0.10117 0.09543 -0.0107 0.0566 1.0000
18.000 1.1841 0.10627 0.10073 -0.0127 0.0547 1.0000
18.250 1.2032 0.10751 0.10174 -0.0121 0.0504 1.0000
18.500 1.1837 0.11395 0.10848 -0.0151 0.0500 1.0000
18.750 1.1613 0.12118 0.11601 -0.0187 0.0497 1.0000
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Polar data table (+)
Polar graphs
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