EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 500,000 Max Cl/Cd: 102.13 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e557-il-500000.txt Download as CSV file: xf-e557-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5837 0.11042 0.10769 -0.0507 1.0000 0.0091
-15.000 -0.6225 0.09771 0.09480 -0.0574 1.0000 0.0089
-14.750 -0.6503 0.08841 0.08533 -0.0624 1.0000 0.0088
-14.500 -0.6761 0.08022 0.07695 -0.0667 1.0000 0.0088
-14.250 -0.6989 0.07321 0.06975 -0.0701 1.0000 0.0085
-14.000 -0.7133 0.06799 0.06439 -0.0725 1.0000 0.0086
-13.750 -0.7267 0.06326 0.05953 -0.0743 1.0000 0.0087
-13.500 -0.7422 0.05863 0.05472 -0.0757 1.0000 0.0085
-13.250 -0.7516 0.05520 0.05118 -0.0763 1.0000 0.0085
-13.000 -0.7618 0.05192 0.04778 -0.0765 1.0000 0.0086
-12.750 -0.7707 0.04901 0.04476 -0.0762 1.0000 0.0086
-12.500 -0.7783 0.04650 0.04216 -0.0757 1.0000 0.0088
-12.250 -0.7870 0.04415 0.03971 -0.0744 1.0000 0.0087
-12.000 -0.7962 0.04207 0.03756 -0.0728 1.0000 0.0088
-11.750 -0.8067 0.04024 0.03565 -0.0707 1.0000 0.0089
-11.500 -0.8041 0.03811 0.03341 -0.0711 0.9987 0.0089
-11.250 -0.7833 0.03568 0.03081 -0.0753 0.9953 0.0094
-11.000 -0.7624 0.03361 0.02861 -0.0785 0.9918 0.0095
-10.750 -0.7414 0.03168 0.02653 -0.0815 0.9871 0.0097
-10.500 -0.7234 0.02936 0.02417 -0.0844 0.9828 0.0101
-10.250 -0.7026 0.02738 0.02212 -0.0872 0.9763 0.0103
-10.000 -0.6702 0.02556 0.02025 -0.0919 0.9734 0.0109
-9.750 -0.6460 0.02373 0.01834 -0.0949 0.9665 0.0114
-9.500 -0.6120 0.02210 0.01660 -0.0991 0.9632 0.0120
-9.250 -0.5775 0.02030 0.01472 -0.1036 0.9611 0.0129
-9.000 -0.5529 0.01918 0.01356 -0.1048 0.9540 0.0136
-8.750 -0.5181 0.01827 0.01257 -0.1074 0.9512 0.0152
-8.500 -0.4820 0.01703 0.01131 -0.1109 0.9491 0.0176
-8.250 -0.4445 0.01599 0.01024 -0.1141 0.9476 0.0206
-8.000 -0.4182 0.01512 0.00934 -0.1149 0.9405 0.0243
-7.750 -0.3824 0.01425 0.00846 -0.1174 0.9374 0.0298
-7.500 -0.3438 0.01350 0.00770 -0.1204 0.9352 0.0376
-7.250 -0.3028 0.01265 0.00690 -0.1239 0.9333 0.0492
-7.000 -0.2719 0.01201 0.00630 -0.1252 0.9259 0.0645
-6.750 -0.2316 0.01121 0.00562 -0.1287 0.9218 0.0933
-6.500 -0.1864 0.01025 0.00488 -0.1334 0.9188 0.1480
-6.250 -0.1515 0.00889 0.00404 -0.1366 0.9107 0.2706
-6.000 -0.1105 0.00846 0.00378 -0.1398 0.9046 0.3436
-5.750 -0.0757 0.00837 0.00367 -0.1413 0.8959 0.3676
-5.500 -0.0382 0.00835 0.00357 -0.1432 0.8878 0.3838
-5.250 -0.0069 0.00837 0.00352 -0.1438 0.8772 0.3963
-5.000 0.0269 0.00843 0.00346 -0.1450 0.8679 0.4066
-4.750 0.0572 0.00845 0.00343 -0.1454 0.8571 0.4141
-4.500 0.0870 0.00852 0.00339 -0.1456 0.8465 0.4211
-4.250 0.1177 0.00854 0.00332 -0.1461 0.8366 0.4269
-4.000 0.1458 0.00861 0.00334 -0.1461 0.8255 0.4331
-3.750 0.1745 0.00875 0.00339 -0.1461 0.8151 0.4425
-3.250 0.2309 0.00885 0.00338 -0.1460 0.7943 0.4523
-3.000 0.2594 0.00887 0.00330 -0.1461 0.7842 0.4555
-2.750 0.2875 0.00886 0.00319 -0.1461 0.7740 0.4582
-2.500 0.3148 0.00882 0.00313 -0.1459 0.7636 0.4609
-2.250 0.3428 0.00884 0.00309 -0.1458 0.7539 0.4638
-2.000 0.3702 0.00886 0.00306 -0.1457 0.7436 0.4669
-1.750 0.3980 0.00888 0.00302 -0.1456 0.7338 0.4700
-1.500 0.4259 0.00894 0.00297 -0.1456 0.7242 0.4728
-1.250 0.4532 0.00891 0.00293 -0.1454 0.7142 0.4756
-1.000 0.4807 0.00894 0.00292 -0.1453 0.7050 0.4786
-0.750 0.5079 0.00897 0.00293 -0.1451 0.6950 0.4817
-0.500 0.5353 0.00901 0.00293 -0.1450 0.6857 0.4849
-0.250 0.5627 0.00907 0.00293 -0.1449 0.6762 0.4881
0.000 0.5901 0.00912 0.00293 -0.1447 0.6666 0.4909
0.250 0.6172 0.00915 0.00294 -0.1445 0.6575 0.4941
0.500 0.6442 0.00918 0.00298 -0.1443 0.6477 0.4975
0.750 0.6712 0.00926 0.00303 -0.1441 0.6385 0.5011
1.000 0.6982 0.00933 0.00307 -0.1439 0.6288 0.5046
1.250 0.7253 0.00942 0.00311 -0.1437 0.6194 0.5078
1.500 0.7518 0.00946 0.00315 -0.1435 0.6099 0.5112
1.750 0.7786 0.00952 0.00323 -0.1432 0.6003 0.5147
2.000 0.8050 0.00963 0.00331 -0.1429 0.5910 0.5186
2.250 0.8316 0.00972 0.00338 -0.1426 0.5809 0.5227
2.500 0.8579 0.00980 0.00347 -0.1423 0.5712 0.5266
2.750 0.8838 0.00990 0.00356 -0.1419 0.5611 0.5305
3.000 0.9099 0.00999 0.00367 -0.1416 0.5508 0.5346
3.250 0.9357 0.01014 0.00378 -0.1412 0.5408 0.5390
3.500 0.9614 0.01024 0.00389 -0.1408 0.5302 0.5432
3.750 0.9870 0.01034 0.00402 -0.1403 0.5199 0.5478
4.000 1.0120 0.01051 0.00417 -0.1398 0.5098 0.5530
4.250 1.0376 0.01064 0.00430 -0.1393 0.4992 0.5581
4.500 1.0626 0.01076 0.00446 -0.1388 0.4889 0.5630
5.000 1.1120 0.01109 0.00480 -0.1376 0.4674 0.5743
5.250 1.1363 0.01125 0.00499 -0.1370 0.4565 0.5800
5.500 1.1597 0.01146 0.00520 -0.1362 0.4453 0.5868
5.750 1.1837 0.01163 0.00540 -0.1355 0.4334 0.5936
6.000 1.2072 0.01182 0.00563 -0.1347 0.4218 0.6007
6.250 1.2299 0.01206 0.00586 -0.1338 0.4099 0.6085
6.500 1.2517 0.01230 0.00612 -0.1327 0.3973 0.6162
6.750 1.2740 0.01254 0.00637 -0.1317 0.3842 0.6254
7.000 1.2954 0.01278 0.00666 -0.1306 0.3710 0.6348
7.250 1.3150 0.01306 0.00695 -0.1291 0.3567 0.6451
7.500 1.3337 0.01336 0.00727 -0.1275 0.3419 0.6565
7.750 1.3518 0.01370 0.00762 -0.1258 0.3262 0.6683
8.000 1.3692 0.01408 0.00801 -0.1239 0.3097 0.6814
8.250 1.3856 0.01452 0.00844 -0.1220 0.2918 0.6963
8.500 1.4007 0.01502 0.00893 -0.1199 0.2728 0.7136
8.750 1.4150 0.01556 0.00946 -0.1177 0.2534 0.7336
9.000 1.4286 0.01612 0.01004 -0.1154 0.2342 0.7573
9.250 1.4407 0.01673 0.01066 -0.1129 0.2162 0.7869
9.500 1.4508 0.01734 0.01133 -0.1101 0.1995 0.8293
9.750 1.4532 0.01771 0.01186 -0.1056 0.1859 1.0000
10.000 1.4644 0.01855 0.01263 -0.1034 0.1703 1.0000
10.250 1.4748 0.01944 0.01346 -0.1011 0.1558 1.0000
10.500 1.4849 0.02037 0.01435 -0.0988 0.1430 1.0000
10.750 1.4944 0.02136 0.01530 -0.0966 0.1313 1.0000
11.000 1.5027 0.02245 0.01635 -0.0944 0.1205 1.0000
11.250 1.5104 0.02361 0.01749 -0.0922 0.1104 1.0000
11.500 1.5192 0.02475 0.01863 -0.0902 0.1015 1.0000
11.750 1.5260 0.02607 0.01995 -0.0882 0.0933 1.0000
12.000 1.5313 0.02755 0.02140 -0.0862 0.0854 1.0000
12.250 1.5387 0.02894 0.02283 -0.0845 0.0788 1.0000
12.500 1.5421 0.03070 0.02458 -0.0826 0.0723 1.0000
12.750 1.5485 0.03228 0.02620 -0.0811 0.0668 1.0000
13.000 1.5510 0.03426 0.02820 -0.0795 0.0614 1.0000
13.250 1.5557 0.03614 0.03012 -0.0783 0.0566 1.0000
13.500 1.5565 0.03844 0.03244 -0.0770 0.0523 1.0000
13.750 1.5606 0.04052 0.03458 -0.0760 0.0483 1.0000
14.000 1.5585 0.04331 0.03739 -0.0750 0.0446 1.0000
14.250 1.5630 0.04552 0.03968 -0.0743 0.0417 1.0000
14.500 1.5619 0.04841 0.04260 -0.0737 0.0388 1.0000
14.750 1.5613 0.05136 0.04563 -0.0732 0.0363 1.0000
15.000 1.5624 0.05421 0.04855 -0.0730 0.0339 1.0000
15.250 1.5582 0.05780 0.05220 -0.0729 0.0319 1.0000
15.500 1.5567 0.06119 0.05568 -0.0730 0.0301 1.0000
15.750 1.5565 0.06449 0.05908 -0.0733 0.0284 1.0000
16.000 1.5520 0.06849 0.06313 -0.0738 0.0269 1.0000
16.250 1.5448 0.07296 0.06769 -0.0746 0.0256 1.0000
16.500 1.5445 0.07657 0.07142 -0.0753 0.0243 1.0000
16.750 1.5414 0.08068 0.07561 -0.0762 0.0231 1.0000
17.000 1.5342 0.08550 0.08051 -0.0776 0.0221 1.0000
17.250 1.5249 0.09077 0.08587 -0.0792 0.0212 1.0000
17.500 1.5232 0.09492 0.09014 -0.0805 0.0202 1.0000
17.750 1.5193 0.09949 0.09481 -0.0821 0.0193 1.0000
18.000 1.5131 0.10451 0.09992 -0.0840 0.0186 1.0000
18.250 1.5031 0.11023 0.10573 -0.0863 0.0179 1.0000
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Polar data table (+)
Polar graphs
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