EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 50,000 Max Cl/Cd: 7.51 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e580-il-50000.txt Download as CSV file: xf-e580-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 580 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3084 0.12221 0.11602 -0.0254 1.0000 0.3115
-8.750 -0.3119 0.12014 0.11403 -0.0235 1.0000 0.3191
-8.500 -0.3441 0.12131 0.11538 -0.0206 1.0000 0.3304
-8.250 -0.3172 0.11658 0.11064 -0.0191 1.0000 0.3379
-7.750 -0.3345 0.11408 0.10833 -0.0142 1.0000 0.3583
-7.500 -0.3395 0.11219 0.10653 -0.0120 1.0000 0.3652
-7.250 -0.3655 0.11245 0.10694 -0.0087 1.0000 0.3771
-6.750 -0.3646 0.10794 0.10254 -0.0049 1.0000 0.3890
-6.000 -0.5898 0.07004 0.06428 -0.0467 1.0000 0.1595
-5.750 -0.5749 0.06352 0.05722 -0.0512 1.0000 0.1415
-5.500 -0.5504 0.05754 0.05021 -0.0571 1.0000 0.1276
-5.250 -0.5330 0.05405 0.04670 -0.0574 1.0000 0.1243
-5.000 -0.5092 0.05053 0.04272 -0.0595 1.0000 0.1196
-4.750 -0.4799 0.04744 0.03883 -0.0619 1.0000 0.1148
-4.500 -0.4534 0.04576 0.03655 -0.0629 1.0000 0.1129
-4.250 -0.4304 0.04409 0.03453 -0.0632 1.0000 0.1127
-4.000 -0.4094 0.04232 0.03269 -0.0631 1.0000 0.1145
-3.750 -0.3896 0.04119 0.03156 -0.0626 1.0000 0.1184
-3.500 -0.3695 0.04040 0.03066 -0.0619 1.0000 0.1222
-3.250 -0.3498 0.03982 0.02991 -0.0607 1.0000 0.1261
-3.000 -0.3327 0.03927 0.02938 -0.0589 1.0000 0.1299
-2.750 -0.2836 0.03960 0.02968 -0.0619 0.9868 0.1430
-2.500 -0.2370 0.03893 0.02943 -0.0663 0.9756 0.1787
-2.250 -0.2221 0.04039 0.03345 -0.0595 0.9678 0.6134
-2.000 -0.2302 0.04268 0.03572 -0.0486 0.9620 0.6655
-1.750 -0.2392 0.04423 0.03730 -0.0381 0.9558 0.7100
-1.500 -0.2513 0.04504 0.03813 -0.0280 0.9515 0.7522
-1.250 -0.2656 0.04552 0.03863 -0.0170 0.9478 0.7970
-1.000 -0.2798 0.04537 0.03848 -0.0066 0.9439 0.8353
-0.750 -0.2887 0.04490 0.03795 0.0012 0.9415 0.8701
-0.500 -0.2846 0.04454 0.03746 0.0057 0.9380 0.8987
-0.250 -0.2550 0.04476 0.03738 0.0038 0.9284 0.9110
0.000 -0.2299 0.04495 0.03734 0.0017 0.9220 0.9182
0.250 -0.1992 0.04529 0.03744 -0.0010 0.9125 0.9249
0.500 -0.1619 0.04600 0.03790 -0.0050 0.9024 0.9314
0.750 -0.1404 0.04624 0.03799 -0.0066 0.8971 0.9372
1.000 -0.1029 0.04702 0.03858 -0.0106 0.8862 0.9436
1.250 -0.0766 0.04759 0.03903 -0.0132 0.8802 0.9495
1.500 -0.0391 0.04849 0.03975 -0.0173 0.8693 0.9560
1.750 0.0080 0.04966 0.04077 -0.0229 0.8573 0.9625
2.000 0.0310 0.05041 0.04145 -0.0253 0.8513 0.9695
2.250 0.0748 0.05159 0.04252 -0.0306 0.8389 0.9770
2.500 0.1046 0.05264 0.04353 -0.0341 0.8323 0.9880
2.750 0.1291 0.05363 0.04444 -0.0365 0.8241 1.0000
3.000 0.1434 0.05478 0.04554 -0.0378 0.8214 1.0000
3.250 0.1490 0.05648 0.04725 -0.0390 0.8334 1.0000
3.500 0.1797 0.05835 0.04906 -0.0429 0.8297 1.0000
3.750 0.2095 0.06049 0.05115 -0.0467 0.8274 1.0000
4.000 0.2382 0.06165 0.05227 -0.0494 0.8099 1.0000
4.250 0.2724 0.06318 0.05375 -0.0529 0.7939 1.0000
4.500 0.3065 0.06474 0.05527 -0.0563 0.7778 1.0000
4.750 0.3647 0.06586 0.05632 -0.0614 0.7492 1.0000
5.000 0.3770 0.06810 0.05858 -0.0633 0.7477 1.0000
5.250 0.3942 0.07063 0.06114 -0.0659 0.7478 1.0000
5.500 0.4280 0.07242 0.06293 -0.0691 0.7326 1.0000
5.750 0.4499 0.07540 0.06595 -0.0725 0.7341 1.0000
6.000 0.4783 0.07715 0.06772 -0.0749 0.7180 1.0000
6.250 0.5314 0.07788 0.06844 -0.0784 0.6885 1.0000
6.500 0.5374 0.08082 0.07145 -0.0799 0.6864 1.0000
6.750 0.5561 0.08425 0.07494 -0.0829 0.6884 1.0000
7.000 0.5795 0.08607 0.07679 -0.0846 0.6713 1.0000
7.250 0.6083 0.08820 0.07897 -0.0870 0.6576 1.0000
7.500 0.6231 0.09173 0.08258 -0.0894 0.6567 1.0000
7.750 0.6616 0.09200 0.08288 -0.0904 0.6247 1.0000
8.000 0.6662 0.09580 0.08675 -0.0921 0.6246 1.0000
8.250 0.7190 0.09578 0.08680 -0.0937 0.5946 1.0000
8.500 0.7111 0.09995 0.09103 -0.0946 0.5930 1.0000
8.750 0.7142 0.10403 0.09519 -0.0962 0.5930 1.0000
9.000 0.7343 0.10649 0.09773 -0.0975 0.5802 1.0000
9.250 0.7804 0.10613 0.09742 -0.0977 0.5485 1.0000
9.500 0.7700 0.11055 0.10191 -0.0985 0.5451 1.0000
9.750 0.7701 0.11502 0.10648 -0.1000 0.5452 1.0000
10.000 0.7849 0.11791 0.10946 -0.1011 0.5345 1.0000
10.250 0.7958 0.12223 0.11388 -0.1029 0.5331 1.0000
10.500 0.8451 0.11956 0.11128 -0.1008 0.4873 1.0000
10.750 0.8764 0.12069 0.11253 -0.1009 0.4703 1.0000
11.000 0.8520 0.12653 0.11843 -0.1022 0.4671 1.0000
11.250 0.8454 0.13130 0.12327 -0.1037 0.4639 1.0000
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Polar data table (+)
Polar graphs
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