EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 50,000 Max Cl/Cd: 32.35 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e557-il-50000-n5.txt Download as CSV file: xf-e557-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4661 0.09786 0.09046 -0.0633 1.0000 0.0454
-11.750 -0.4862 0.09105 0.08364 -0.0664 1.0000 0.0451
-11.500 -0.5083 0.08468 0.07723 -0.0691 1.0000 0.0449
-11.250 -0.5294 0.07917 0.07167 -0.0712 1.0000 0.0446
-11.000 -0.5506 0.07428 0.06671 -0.0727 1.0000 0.0445
-10.750 -0.5730 0.06984 0.06221 -0.0735 1.0000 0.0445
-10.500 -0.5924 0.06626 0.05854 -0.0733 1.0000 0.0444
-10.250 -0.6126 0.06318 0.05537 -0.0723 1.0000 0.0445
-10.000 -0.6332 0.06062 0.05272 -0.0704 1.0000 0.0446
-9.750 -0.6536 0.05831 0.05030 -0.0682 1.0000 0.0448
-9.500 -0.6679 0.05566 0.04745 -0.0668 1.0000 0.0452
-9.250 -0.6699 0.05373 0.04552 -0.0650 1.0000 0.0464
-9.000 -0.6704 0.05200 0.04376 -0.0632 1.0000 0.0479
-8.750 -0.6703 0.05016 0.04180 -0.0616 1.0000 0.0498
-8.500 -0.6677 0.04818 0.03958 -0.0599 1.0000 0.0520
-8.250 -0.6611 0.04638 0.03759 -0.0579 1.0000 0.0543
-8.000 -0.6536 0.04513 0.03639 -0.0560 1.0000 0.0572
-7.750 -0.6451 0.04381 0.03492 -0.0541 1.0000 0.0610
-7.500 -0.6276 0.04250 0.03357 -0.0533 0.9977 0.0659
-7.250 -0.5984 0.04112 0.03197 -0.0548 0.9916 0.0744
-7.000 -0.5715 0.03967 0.03058 -0.0565 0.9850 0.0838
-6.750 -0.5459 0.03802 0.02895 -0.0585 0.9777 0.0962
-6.500 -0.5180 0.03618 0.02712 -0.0613 0.9706 0.1143
-6.250 -0.4896 0.03380 0.02491 -0.0654 0.9631 0.1430
-6.000 -0.4589 0.03089 0.02264 -0.0709 0.9561 0.2058
-5.750 -0.4268 0.03122 0.02387 -0.0719 0.9488 0.3289
-5.500 -0.3947 0.03218 0.02456 -0.0725 0.9401 0.3843
-5.250 -0.3582 0.03337 0.02547 -0.0733 0.9332 0.4178
-5.000 -0.3310 0.03398 0.02582 -0.0731 0.9238 0.4416
-4.750 -0.2984 0.03511 0.02678 -0.0724 0.9174 0.4604
-4.500 -0.2756 0.03575 0.02728 -0.0708 0.9077 0.4767
-4.250 -0.2425 0.03627 0.02762 -0.0709 0.9015 0.4930
-4.000 -0.2195 0.03645 0.02764 -0.0698 0.8919 0.5044
-3.500 -0.1574 0.03580 0.02657 -0.0723 0.8765 0.5230
-3.250 -0.1213 0.03548 0.02607 -0.0739 0.8710 0.5287
-3.000 -0.0973 0.03520 0.02565 -0.0739 0.8612 0.5347
-2.750 -0.0554 0.03444 0.02463 -0.0779 0.8556 0.5423
-2.500 -0.0324 0.03431 0.02440 -0.0773 0.8460 0.5463
-2.250 0.0049 0.03386 0.02378 -0.0796 0.8400 0.5520
-2.000 0.0372 0.03337 0.02309 -0.0820 0.8313 0.5585
-1.750 0.0699 0.03310 0.02273 -0.0828 0.8246 0.5623
-1.500 0.0990 0.03288 0.02243 -0.0835 0.8164 0.5671
-1.250 0.1359 0.03246 0.02183 -0.0861 0.8092 0.5733
-1.000 0.1711 0.03214 0.02143 -0.0877 0.8028 0.5776
-0.750 0.1970 0.03206 0.02130 -0.0877 0.7935 0.5820
-0.500 0.2410 0.03158 0.02070 -0.0909 0.7890 0.5881
-0.250 0.2632 0.03161 0.02067 -0.0908 0.7779 0.5929
0.000 0.3033 0.03125 0.02026 -0.0927 0.7730 0.5974
0.250 0.3243 0.03137 0.02036 -0.0922 0.7619 0.6026
0.500 0.3692 0.03095 0.01985 -0.0955 0.7569 0.6091
0.750 0.3877 0.03115 0.02007 -0.0943 0.7458 0.6131
1.000 0.4293 0.03079 0.01968 -0.0966 0.7406 0.6189
1.250 0.4529 0.03100 0.01986 -0.0967 0.7296 0.6252
1.500 0.4911 0.03067 0.01955 -0.0981 0.7241 0.6303
1.750 0.5114 0.03098 0.01987 -0.0974 0.7130 0.6361
2.000 0.5540 0.03061 0.01949 -0.0998 0.7075 0.6429
2.250 0.5710 0.03100 0.01994 -0.0984 0.6962 0.6481
2.500 0.6137 0.03064 0.01956 -0.1008 0.6908 0.6558
3.000 0.6682 0.03085 0.01988 -0.1008 0.6731 0.6689
3.250 0.6886 0.03126 0.02035 -0.1001 0.6620 0.6761
3.500 0.7161 0.03135 0.02051 -0.1000 0.6537 0.6833
3.750 0.7453 0.03146 0.02069 -0.1005 0.6447 0.6919
4.000 0.7668 0.03177 0.02110 -0.0995 0.6351 0.6994
4.250 0.8007 0.03168 0.02110 -0.1004 0.6272 0.7089
4.500 0.8178 0.03217 0.02170 -0.0990 0.6166 0.7176
4.750 0.8551 0.03189 0.02150 -0.1000 0.6096 0.7281
5.000 0.8697 0.03254 0.02227 -0.0984 0.5980 0.7386
5.250 0.9006 0.03242 0.02228 -0.0985 0.5901 0.7501
5.500 0.9195 0.03279 0.02280 -0.0972 0.5794 0.7624
5.750 0.9380 0.03320 0.02335 -0.0958 0.5691 0.7761
6.000 0.9708 0.03290 0.02318 -0.0960 0.5607 0.7924
6.250 0.9800 0.03356 0.02403 -0.0934 0.5490 0.8095
6.500 1.0019 0.03357 0.02420 -0.0920 0.5394 0.8318
6.750 1.0209 0.03354 0.02436 -0.0901 0.5294 0.8620
7.000 1.0255 0.03398 0.02500 -0.0866 0.5180 0.9286
7.250 1.0588 0.03410 0.02518 -0.0879 0.5067 1.0000
7.500 1.0961 0.03411 0.02523 -0.0894 0.4953 1.0000
7.750 1.1096 0.03502 0.02622 -0.0880 0.4822 1.0000
8.000 1.1276 0.03573 0.02700 -0.0871 0.4694 1.0000
8.250 1.1503 0.03617 0.02749 -0.0865 0.4569 1.0000
8.500 1.1766 0.03638 0.02775 -0.0861 0.4442 1.0000
8.750 1.1945 0.03693 0.02837 -0.0849 0.4308 1.0000
9.000 1.2030 0.03799 0.02951 -0.0827 0.4170 1.0000
9.250 1.2130 0.03896 0.03057 -0.0808 0.4030 1.0000
9.500 1.2239 0.03992 0.03162 -0.0790 0.3889 1.0000
9.750 1.2346 0.04088 0.03265 -0.0772 0.3747 1.0000
10.000 1.2446 0.04192 0.03374 -0.0754 0.3602 1.0000
10.250 1.2535 0.04305 0.03493 -0.0737 0.3456 1.0000
10.500 1.2612 0.04431 0.03624 -0.0719 0.3310 1.0000
10.750 1.2678 0.04571 0.03769 -0.0703 0.3163 1.0000
11.000 1.2734 0.04724 0.03925 -0.0687 0.3017 1.0000
11.250 1.2761 0.04911 0.04119 -0.0671 0.2873 1.0000
11.500 1.2762 0.05134 0.04349 -0.0657 0.2732 1.0000
11.750 1.2766 0.05367 0.04589 -0.0646 0.2596 1.0000
12.000 1.2770 0.05609 0.04837 -0.0636 0.2463 1.0000
12.250 1.2779 0.05856 0.05090 -0.0627 0.2335 1.0000
12.500 1.2799 0.06098 0.05333 -0.0619 0.2214 1.0000
12.750 1.2830 0.06328 0.05559 -0.0612 0.2096 1.0000
13.000 1.2786 0.06673 0.05919 -0.0610 0.1985 1.0000
13.250 1.2766 0.06998 0.06251 -0.0608 0.1881 1.0000
13.500 1.2787 0.07266 0.06517 -0.0606 0.1781 1.0000
13.750 1.2748 0.07637 0.06901 -0.0608 0.1687 1.0000
14.000 1.2719 0.08004 0.07278 -0.0612 0.1601 1.0000
14.250 1.2750 0.08278 0.07551 -0.0612 0.1515 1.0000
14.500 1.2659 0.08770 0.08066 -0.0623 0.1442 1.0000
14.750 1.2720 0.09002 0.08287 -0.0623 0.1363 1.0000
15.000 1.2586 0.09596 0.08913 -0.0642 0.1303 1.0000
15.250 1.2646 0.09835 0.09146 -0.0645 0.1232 1.0000
15.500 1.2501 0.10477 0.09815 -0.0669 0.1182 1.0000
15.750 1.2443 0.10961 0.10313 -0.0687 0.1128 1.0000
16.000 1.2454 0.11317 0.10671 -0.0699 0.1075 1.0000
16.250 1.2228 0.12172 0.11557 -0.0742 0.1040 1.0000
16.500 1.2123 0.12793 0.12192 -0.0773 0.0999 1.0000
16.750 1.2198 0.13028 0.12424 -0.0780 0.0952 1.0000
17.000 1.1756 0.14485 0.13911 -0.0869 0.0939 1.0000
17.250 1.0998 0.17045 0.16471 -0.1030 0.0919 1.0000
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Polar data table (+)
Polar graphs
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