EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 50,000 Max Cl/Cd: 18.05 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e554-il-50000-n5.txt Download as CSV file: xf-e554-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5009 0.10200 0.09443 -0.0561 1.0000 0.0439
-13.250 -0.5203 0.09472 0.08706 -0.0599 1.0000 0.0436
-13.000 -0.5400 0.08809 0.08032 -0.0632 1.0000 0.0433
-12.750 -0.5606 0.08184 0.07391 -0.0662 1.0000 0.0432
-12.500 -0.5785 0.07637 0.06827 -0.0685 1.0000 0.0433
-12.250 -0.5915 0.07181 0.06352 -0.0701 1.0000 0.0435
-12.000 -0.6034 0.06751 0.05899 -0.0711 1.0000 0.0439
-11.750 -0.6016 0.06465 0.05606 -0.0709 1.0000 0.0448
-11.500 -0.5972 0.06230 0.05367 -0.0705 1.0000 0.0461
-11.250 -0.5944 0.05986 0.05113 -0.0701 1.0000 0.0477
-11.000 -0.5913 0.05739 0.04844 -0.0694 1.0000 0.0498
-10.750 -0.5818 0.05559 0.04660 -0.0682 1.0000 0.0524
-10.500 -0.5704 0.05408 0.04504 -0.0668 1.0000 0.0554
-10.250 -0.5597 0.05253 0.04335 -0.0652 1.0000 0.0592
-10.000 -0.5513 0.05123 0.04216 -0.0636 1.0000 0.0631
-9.750 -0.5427 0.04993 0.04078 -0.0617 1.0000 0.0681
-9.500 -0.5391 0.04861 0.03960 -0.0599 1.0000 0.0730
-9.250 -0.5358 0.04736 0.03838 -0.0576 1.0000 0.0789
-9.000 -0.5386 0.04604 0.03720 -0.0552 1.0000 0.0846
-8.750 -0.5444 0.04487 0.03611 -0.0522 1.0000 0.0904
-8.500 -0.5589 0.04384 0.03525 -0.0485 1.0000 0.0942
-8.250 -0.5727 0.04285 0.03432 -0.0452 0.9972 0.0996
-8.000 -0.5538 0.04005 0.03172 -0.0494 0.9749 0.1175
-7.750 -0.5402 0.03676 0.02865 -0.0537 0.9516 0.1443
-7.500 -0.5285 0.03327 0.02561 -0.0579 0.9307 0.1899
-7.250 -0.5007 0.03346 0.02702 -0.0575 0.9151 0.3081
-7.000 -0.4673 0.03329 0.02650 -0.0606 0.8992 0.3797
-6.750 -0.4255 0.03492 0.02784 -0.0614 0.8855 0.4158
-6.500 -0.3817 0.03663 0.02924 -0.0616 0.8733 0.4406
-6.250 -0.3470 0.03689 0.02917 -0.0629 0.8598 0.4630
-6.000 -0.3049 0.03863 0.03069 -0.0615 0.8462 0.4753
-5.750 -0.2695 0.03915 0.03097 -0.0612 0.8326 0.4874
-5.500 -0.2428 0.03860 0.03014 -0.0620 0.8191 0.5003
-5.250 -0.2089 0.03862 0.02990 -0.0621 0.8068 0.5083
-5.000 -0.1899 0.03776 0.02881 -0.0623 0.7925 0.5178
-4.500 -0.1433 0.03633 0.02688 -0.0631 0.7689 0.5336
-4.250 -0.1179 0.03624 0.02664 -0.0621 0.7569 0.5374
-4.000 -0.0948 0.03579 0.02601 -0.0619 0.7461 0.5428
-3.750 -0.0742 0.03466 0.02461 -0.0632 0.7363 0.5511
-3.500 -0.0511 0.03452 0.02437 -0.0624 0.7258 0.5544
-3.250 -0.0235 0.03414 0.02380 -0.0626 0.7176 0.5587
-3.000 -0.0036 0.03362 0.02312 -0.0628 0.7075 0.5646
-2.750 0.0232 0.03297 0.02226 -0.0639 0.7001 0.5700
-2.500 0.0448 0.03286 0.02209 -0.0632 0.6909 0.5733
-2.250 0.0715 0.03256 0.02164 -0.0635 0.6839 0.5776
-2.000 0.0947 0.03220 0.02114 -0.0640 0.6758 0.5832
-1.750 0.1203 0.03185 0.02065 -0.0647 0.6684 0.5878
-1.500 0.1474 0.03171 0.02039 -0.0647 0.6625 0.5912
-1.250 0.1686 0.03169 0.02036 -0.0643 0.6547 0.5954
-1.000 0.1967 0.03144 0.01995 -0.0652 0.6489 0.6007
-0.750 0.2219 0.03131 0.01973 -0.0658 0.6425 0.6054
-0.500 0.2441 0.03138 0.01979 -0.0653 0.6357 0.6087
-0.250 0.2720 0.03129 0.01961 -0.0656 0.6306 0.6130
0.000 0.2958 0.03136 0.01963 -0.0659 0.6247 0.6184
0.250 0.3192 0.03147 0.01971 -0.0661 0.6185 0.6232
0.500 0.3456 0.03150 0.01971 -0.0660 0.6138 0.6270
0.750 0.3700 0.03164 0.01982 -0.0660 0.6087 0.6316
1.000 0.3908 0.03195 0.02013 -0.0660 0.6022 0.6371
1.250 0.4169 0.03208 0.02024 -0.0662 0.5976 0.6419
1.500 0.4456 0.03213 0.02025 -0.0664 0.5941 0.6466
1.750 0.4604 0.03279 0.02100 -0.0656 0.5873 0.6519
2.000 0.4850 0.03310 0.02130 -0.0660 0.5821 0.6577
2.250 0.5118 0.03325 0.02146 -0.0658 0.5783 0.6623
2.500 0.5326 0.03376 0.02201 -0.0655 0.5736 0.6681
2.750 0.5490 0.03456 0.02287 -0.0651 0.5673 0.6747
3.000 0.5720 0.03490 0.02325 -0.0646 0.5630 0.6797
3.250 0.6024 0.03501 0.02337 -0.0651 0.5597 0.6863
3.500 0.6096 0.03633 0.02481 -0.0638 0.5529 0.6927
3.750 0.6257 0.03707 0.02565 -0.0627 0.5477 0.6986
4.000 0.6541 0.03733 0.02594 -0.0632 0.5440 0.7065
4.250 0.6715 0.03810 0.02680 -0.0624 0.5393 0.7134
4.500 0.6711 0.03984 0.02868 -0.0602 0.5319 0.7204
4.750 0.6961 0.04027 0.02917 -0.0602 0.5279 0.7289
5.000 0.7274 0.04029 0.02926 -0.0605 0.5250 0.7379
5.500 0.7260 0.04395 0.03320 -0.0564 0.5109 0.7557
5.750 0.7582 0.04387 0.03321 -0.0566 0.5081 0.7669
6.000 0.7161 0.04825 0.03772 -0.0521 0.4961 0.7763
6.250 0.7426 0.04834 0.03795 -0.0516 0.4928 0.7898
6.500 0.7771 0.04791 0.03764 -0.0515 0.4905 0.8057
7.000 0.7605 0.05297 0.04301 -0.0476 0.4743 0.8429
7.500 0.7549 0.05775 0.04816 -0.0459 0.4578 1.0000
8.000 0.7715 0.06284 0.05328 -0.0479 0.4417 1.0000
8.500 0.7875 0.06762 0.05813 -0.0490 0.4258 1.0000
8.750 0.8248 0.06719 0.05774 -0.0492 0.4231 1.0000
9.250 0.8389 0.07183 0.06247 -0.0496 0.4069 1.0000
9.500 0.8208 0.07665 0.06735 -0.0502 0.3940 1.0000
9.750 0.8546 0.07623 0.06700 -0.0499 0.3907 1.0000
10.000 0.8382 0.08101 0.07183 -0.0505 0.3780 1.0000
10.250 0.8719 0.08043 0.07134 -0.0501 0.3745 1.0000
10.500 0.8561 0.08527 0.07624 -0.0509 0.3619 1.0000
10.750 0.8907 0.08440 0.07548 -0.0502 0.3584 1.0000
11.000 0.8752 0.08934 0.08048 -0.0512 0.3456 1.0000
11.500 0.8957 0.09318 0.08450 -0.0514 0.3294 1.0000
11.750 0.8891 0.09729 0.08868 -0.0524 0.3183 1.0000
12.000 0.9168 0.09683 0.08835 -0.0517 0.3131 1.0000
12.250 0.9072 0.10150 0.09309 -0.0529 0.3014 1.0000
12.500 0.9385 0.10033 0.09205 -0.0518 0.2970 1.0000
12.750 0.9269 0.10540 0.09719 -0.0533 0.2847 1.0000
13.250 0.9472 0.10914 0.10115 -0.0538 0.2683 1.0000
13.750 0.9682 0.11268 0.10491 -0.0542 0.2521 1.0000
14.250 0.9900 0.11596 0.10842 -0.0546 0.2362 1.0000
14.500 0.9756 0.12235 0.11486 -0.0572 0.2241 1.0000
14.750 1.0074 0.11993 0.11258 -0.0554 0.2198 1.0000
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