EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 200,000 Max Cl/Cd: 70.94 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e558-il-200000-n5.txt Download as CSV file: xf-e558-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 558 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.5830 0.13468 0.13029 -0.0348 1.0000 0.0150
-16.500 -0.6087 0.12476 0.12022 -0.0395 1.0000 0.0148
-16.250 -0.6366 0.11469 0.10994 -0.0447 1.0000 0.0150
-16.000 -0.6504 0.10806 0.10317 -0.0479 1.0000 0.0150
-15.750 -0.6605 0.10241 0.09742 -0.0507 1.0000 0.0151
-15.500 -0.6652 0.09801 0.09297 -0.0526 1.0000 0.0152
-15.250 -0.6701 0.09366 0.08855 -0.0544 1.0000 0.0152
-15.000 -0.6735 0.08969 0.08457 -0.0562 1.0000 0.0156
-14.750 -0.6774 0.08570 0.08051 -0.0578 1.0000 0.0156
-14.500 -0.6815 0.08174 0.07650 -0.0595 1.0000 0.0158
-14.250 -0.6872 0.07754 0.07224 -0.0614 1.0000 0.0162
-14.000 -0.6900 0.07405 0.06870 -0.0627 1.0000 0.0162
-13.750 -0.6946 0.07039 0.06497 -0.0641 1.0000 0.0165
-13.500 -0.6999 0.06680 0.06131 -0.0654 1.0000 0.0168
-13.250 -0.7045 0.06353 0.05799 -0.0663 1.0000 0.0169
-13.000 -0.7093 0.06032 0.05472 -0.0672 1.0000 0.0170
-12.750 -0.7145 0.05717 0.05150 -0.0679 1.0000 0.0172
-12.500 -0.7207 0.05404 0.04831 -0.0686 1.0000 0.0174
-12.250 -0.7272 0.05098 0.04520 -0.0690 1.0000 0.0175
-12.000 -0.7347 0.04796 0.04212 -0.0694 1.0000 0.0177
-11.750 -0.7442 0.04490 0.03900 -0.0695 1.0000 0.0179
-11.500 -0.7546 0.04198 0.03602 -0.0693 1.0000 0.0181
-11.250 -0.7703 0.03894 0.03295 -0.0687 1.0000 0.0182
-11.000 -0.7908 0.03619 0.03015 -0.0672 1.0000 0.0182
-10.750 -0.8080 0.03325 0.02712 -0.0669 1.0000 0.0183
-10.500 -0.7917 0.03062 0.02439 -0.0707 0.9961 0.0188
-10.250 -0.7629 0.02853 0.02218 -0.0750 0.9901 0.0195
-10.000 -0.7328 0.02679 0.02029 -0.0785 0.9842 0.0206
-9.750 -0.7054 0.02526 0.01863 -0.0809 0.9771 0.0219
-9.500 -0.6740 0.02385 0.01714 -0.0837 0.9712 0.0238
-9.250 -0.6484 0.02263 0.01582 -0.0848 0.9619 0.0262
-9.000 -0.6206 0.02151 0.01461 -0.0861 0.9534 0.0294
-8.750 -0.5901 0.02035 0.01339 -0.0879 0.9459 0.0347
-8.500 -0.5635 0.01930 0.01233 -0.0887 0.9357 0.0419
-8.000 -0.5015 0.01739 0.01045 -0.0916 0.9187 0.0710
-7.750 -0.4673 0.01655 0.00966 -0.0935 0.9107 0.0903
-7.500 -0.4319 0.01582 0.00896 -0.0955 0.9016 0.1115
-7.250 -0.3940 0.01516 0.00836 -0.0981 0.8924 0.1374
-7.000 -0.3539 0.01462 0.00785 -0.1009 0.8824 0.1643
-6.750 -0.3157 0.01420 0.00743 -0.1032 0.8698 0.1850
-6.500 -0.2764 0.01388 0.00705 -0.1055 0.8563 0.2021
-6.250 -0.2386 0.01363 0.00671 -0.1075 0.8414 0.2168
-6.000 -0.2035 0.01345 0.00639 -0.1089 0.8251 0.2295
-5.750 -0.1713 0.01330 0.00614 -0.1097 0.8086 0.2408
-5.500 -0.1411 0.01318 0.00591 -0.1101 0.7920 0.2507
-5.250 -0.1120 0.01311 0.00568 -0.1102 0.7756 0.2606
-5.000 -0.0841 0.01301 0.00552 -0.1101 0.7600 0.2693
-4.750 -0.0562 0.01296 0.00532 -0.1099 0.7450 0.2782
-4.500 -0.0288 0.01290 0.00520 -0.1097 0.7308 0.2866
-4.250 -0.0012 0.01287 0.00502 -0.1095 0.7170 0.2951
-4.000 0.0257 0.01282 0.00491 -0.1092 0.7034 0.3027
-3.750 0.0529 0.01280 0.00476 -0.1089 0.6902 0.3111
-3.500 0.0797 0.01276 0.00468 -0.1086 0.6776 0.3183
-3.250 0.1068 0.01277 0.00456 -0.1083 0.6655 0.3263
-3.000 0.1337 0.01274 0.00448 -0.1080 0.6532 0.3333
-2.750 0.1607 0.01273 0.00440 -0.1077 0.6419 0.3410
-2.500 0.1876 0.01275 0.00431 -0.1073 0.6307 0.3483
-2.250 0.2144 0.01273 0.00427 -0.1070 0.6192 0.3555
-2.000 0.2415 0.01276 0.00420 -0.1067 0.6090 0.3633
-1.750 0.2683 0.01276 0.00417 -0.1064 0.5983 0.3701
-1.500 0.2952 0.01279 0.00414 -0.1061 0.5881 0.3780
-1.250 0.3220 0.01282 0.00410 -0.1058 0.5782 0.3853
-1.000 0.3489 0.01284 0.00411 -0.1055 0.5686 0.3926
-0.750 0.3758 0.01291 0.00408 -0.1052 0.5596 0.4009
-0.500 0.4026 0.01291 0.00411 -0.1049 0.5502 0.4083
0.000 0.4561 0.01301 0.00414 -0.1042 0.5326 0.4242
0.250 0.4827 0.01309 0.00417 -0.1039 0.5246 0.4330
0.500 0.5095 0.01313 0.00423 -0.1036 0.5161 0.4412
0.750 0.5359 0.01321 0.00428 -0.1033 0.5082 0.4503
1.000 0.5627 0.01327 0.00435 -0.1030 0.5004 0.4595
1.250 0.5892 0.01335 0.00443 -0.1026 0.4930 0.4691
1.500 0.6156 0.01343 0.00451 -0.1023 0.4860 0.4788
1.750 0.6421 0.01351 0.00461 -0.1020 0.4784 0.4900
2.000 0.6681 0.01362 0.00471 -0.1015 0.4718 0.5010
2.250 0.6948 0.01369 0.00484 -0.1013 0.4650 0.5131
2.500 0.7208 0.01379 0.00497 -0.1009 0.4584 0.5264
2.750 0.7467 0.01390 0.00511 -0.1004 0.4523 0.5406
3.000 0.7728 0.01399 0.00527 -0.1000 0.4455 0.5562
3.250 0.7984 0.01411 0.00542 -0.0996 0.4396 0.5736
3.500 0.8241 0.01422 0.00561 -0.0991 0.4342 0.5935
3.750 0.8497 0.01431 0.00581 -0.0986 0.4280 0.6160
4.000 0.8745 0.01443 0.00599 -0.0980 0.4223 0.6417
4.250 0.8992 0.01454 0.00621 -0.0973 0.4170 0.6720
4.500 0.9233 0.01462 0.00644 -0.0965 0.4115 0.7079
4.750 0.9460 0.01470 0.00666 -0.0954 0.4062 0.7522
5.000 0.9677 0.01477 0.00687 -0.0939 0.4014 0.8101
5.250 0.9905 0.01473 0.00705 -0.0926 0.3958 0.9108
5.500 1.0199 0.01491 0.00724 -0.0930 0.3903 1.0000
6.000 1.0702 0.01542 0.00775 -0.0922 0.3801 1.0000
6.250 1.0949 0.01568 0.00802 -0.0917 0.3747 1.0000
6.500 1.1191 0.01598 0.00828 -0.0911 0.3698 1.0000
6.750 1.1434 0.01625 0.00859 -0.0905 0.3645 1.0000
7.000 1.1673 0.01652 0.00891 -0.0899 0.3589 1.0000
7.250 1.1905 0.01683 0.00920 -0.0892 0.3539 1.0000
7.500 1.2138 0.01714 0.00955 -0.0884 0.3488 1.0000
7.750 1.2365 0.01743 0.00990 -0.0876 0.3430 1.0000
8.000 1.2584 0.01776 0.01024 -0.0867 0.3377 1.0000
8.250 1.2802 0.01810 0.01062 -0.0857 0.3323 1.0000
8.500 1.3013 0.01842 0.01100 -0.0847 0.3261 1.0000
8.750 1.3209 0.01879 0.01137 -0.0834 0.3203 1.0000
9.000 1.3406 0.01913 0.01180 -0.0821 0.3141 1.0000
9.250 1.3582 0.01949 0.01221 -0.0805 0.3077 1.0000
9.500 1.3744 0.01991 0.01263 -0.0786 0.3019 1.0000
9.750 1.3913 0.02030 0.01313 -0.0769 0.2949 1.0000
10.000 1.4059 0.02077 0.01361 -0.0749 0.2884 1.0000
10.250 1.4212 0.02124 0.01416 -0.0731 0.2812 1.0000
10.500 1.4341 0.02178 0.01475 -0.0710 0.2736 1.0000
10.750 1.4470 0.02235 0.01539 -0.0690 0.2656 1.0000
11.000 1.4573 0.02304 0.01609 -0.0667 0.2570 1.0000
11.250 1.4689 0.02374 0.01687 -0.0647 0.2485 1.0000
11.500 1.4764 0.02462 0.01776 -0.0624 0.2401 1.0000
11.750 1.4865 0.02549 0.01872 -0.0605 0.2309 1.0000
12.000 1.4923 0.02659 0.01985 -0.0583 0.2219 1.0000
12.250 1.4968 0.02786 0.02115 -0.0562 0.2115 1.0000
12.500 1.5003 0.02929 0.02261 -0.0543 0.2003 1.0000
12.750 1.5008 0.03102 0.02436 -0.0524 0.1890 1.0000
13.000 1.4987 0.03308 0.02642 -0.0507 0.1776 1.0000
13.250 1.4937 0.03554 0.02887 -0.0491 0.1654 1.0000
13.500 1.4892 0.03815 0.03150 -0.0480 0.1538 1.0000
13.750 1.4838 0.04100 0.03438 -0.0471 0.1431 1.0000
14.000 1.4767 0.04418 0.03758 -0.0465 0.1334 1.0000
14.250 1.4674 0.04777 0.04118 -0.0461 0.1248 1.0000
14.500 1.4623 0.05106 0.04454 -0.0460 0.1170 1.0000
14.750 1.4533 0.05494 0.04846 -0.0462 0.1102 1.0000
15.000 1.4459 0.05878 0.05236 -0.0465 0.1034 1.0000
15.250 1.4367 0.06298 0.05662 -0.0471 0.0979 1.0000
15.500 1.4292 0.06709 0.06081 -0.0478 0.0921 1.0000
15.750 1.4192 0.07169 0.06546 -0.0488 0.0872 1.0000
16.000 1.4125 0.07594 0.06979 -0.0497 0.0821 1.0000
16.250 1.4022 0.08080 0.07472 -0.0511 0.0777 1.0000
16.500 1.3954 0.08528 0.07928 -0.0523 0.0732 1.0000
16.750 1.3866 0.09013 0.08420 -0.0538 0.0690 1.0000
17.000 1.3782 0.09500 0.08915 -0.0554 0.0654 1.0000
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Polar data table (+)
Polar graphs
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