GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 50,000 Max Cl/Cd: 31.62 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe575-il-50000.txt Download as CSV file: xf-goe575-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 575 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4447 0.11391 0.10694 -0.0121 1.0000 0.2809
-8.000 -0.3977 0.10823 0.10118 -0.0100 1.0000 0.2922
-7.750 -0.4505 0.10818 0.10134 -0.0089 1.0000 0.2997
-7.500 -0.4073 0.10316 0.09625 -0.0070 1.0000 0.3137
-7.250 -0.4234 0.10066 0.09387 -0.0053 1.0000 0.3223
-7.000 -0.4299 0.09860 0.09187 -0.0030 1.0000 0.3354
-6.750 -0.4188 0.09517 0.08848 -0.0012 1.0000 0.3458
-6.500 -0.4822 0.09515 0.08868 0.0042 1.0000 0.3564
-6.250 -0.4611 0.09147 0.08502 0.0058 1.0000 0.3740
-6.000 -0.4528 0.08851 0.08211 0.0085 1.0000 0.3913
-5.750 -0.4624 0.08644 0.08013 0.0128 1.0000 0.4107
-5.500 -0.4797 0.08476 0.07857 0.0181 1.0000 0.4307
-5.250 -0.4529 0.08174 0.07557 0.0206 1.0000 0.4664
-5.000 -0.4352 0.07929 0.07315 0.0240 1.0000 0.5028
-4.750 -0.3978 0.07693 0.07079 0.0269 1.0000 0.5568
-3.750 -0.6313 0.05779 0.04983 0.0337 1.0000 0.2077
-3.500 -0.6231 0.05524 0.04728 0.0364 1.0000 0.2022
-3.250 -0.6321 0.05252 0.04373 0.0425 1.0000 0.1887
-3.000 -0.6259 0.05038 0.04151 0.0457 1.0000 0.1871
-2.750 -0.6221 0.04869 0.03958 0.0495 1.0000 0.1867
-2.500 -0.6168 0.04704 0.03768 0.0531 1.0000 0.1861
-2.250 -0.6114 0.04570 0.03601 0.0568 1.0000 0.1869
-2.000 -0.6043 0.04438 0.03434 0.0603 1.0000 0.1876
-1.750 -0.5945 0.04313 0.03279 0.0632 1.0000 0.1880
-1.500 -0.5828 0.04196 0.03129 0.0657 1.0000 0.1891
-1.250 -0.5669 0.04073 0.03002 0.0669 1.0000 0.1920
-1.000 -0.5521 0.04005 0.02931 0.0682 1.0000 0.1983
-0.750 -0.5340 0.03933 0.02831 0.0692 1.0000 0.2035
-0.500 -0.4984 0.03879 0.02756 0.0664 0.9969 0.2114
-0.250 -0.2708 0.03835 0.02718 0.0260 0.9591 0.3168
0.000 -0.1121 0.03724 0.02740 -0.0014 0.9423 0.4929
0.250 0.1181 0.04002 0.03076 -0.0405 0.9338 1.0000
0.500 0.1631 0.03999 0.03050 -0.0444 0.9122 1.0000
0.750 0.2169 0.03995 0.03025 -0.0496 0.8936 1.0000
1.000 0.2596 0.03985 0.02999 -0.0526 0.8741 1.0000
1.250 0.2998 0.03967 0.02969 -0.0551 0.8537 1.0000
1.500 0.3435 0.03936 0.02928 -0.0578 0.8348 1.0000
1.750 0.3878 0.03895 0.02878 -0.0604 0.8167 1.0000
2.000 0.4333 0.03837 0.02813 -0.0629 0.7991 1.0000
2.250 0.4781 0.03773 0.02744 -0.0651 0.7825 1.0000
2.500 0.5254 0.03685 0.02651 -0.0674 0.7666 1.0000
2.750 0.5791 0.03569 0.02533 -0.0706 0.7519 1.0000
3.000 0.6747 0.03300 0.02259 -0.0804 0.7413 1.0000
3.250 0.7438 0.03186 0.02143 -0.0868 0.7221 1.0000
3.500 0.7980 0.03154 0.02108 -0.0910 0.6990 1.0000
3.750 0.8776 0.03095 0.02040 -0.0999 0.6729 1.0000
4.000 0.9410 0.03084 0.02018 -0.1060 0.6472 1.0000
4.250 0.9662 0.03146 0.02077 -0.1052 0.6266 1.0000
4.500 0.9929 0.03211 0.02140 -0.1048 0.6075 1.0000
4.750 1.0186 0.03275 0.02202 -0.1041 0.5894 1.0000
5.000 1.0440 0.03340 0.02264 -0.1033 0.5722 1.0000
5.250 1.0702 0.03407 0.02327 -0.1027 0.5555 1.0000
5.500 1.0980 0.03472 0.02388 -0.1024 0.5391 1.0000
5.750 1.0976 0.03587 0.02515 -0.0970 0.5253 1.0000
6.000 1.1063 0.03697 0.02630 -0.0933 0.5116 1.0000
6.250 1.1242 0.03785 0.02720 -0.0912 0.4972 1.0000
6.500 1.1500 0.03863 0.02796 -0.0906 0.4827 1.0000
6.750 1.1588 0.03981 0.02921 -0.0870 0.4700 1.0000
7.000 1.1549 0.04139 0.03092 -0.0813 0.4590 1.0000
7.250 1.1799 0.04233 0.03185 -0.0806 0.4464 1.0000
7.500 1.1780 0.04387 0.03352 -0.0754 0.4358 1.0000
7.750 1.1790 0.04552 0.03526 -0.0709 0.4261 1.0000
8.000 1.2101 0.04633 0.03606 -0.0712 0.4143 1.0000
8.250 1.1768 0.04906 0.03901 -0.0614 0.4083 1.0000
8.500 1.2223 0.04929 0.03918 -0.0639 0.3947 1.0000
8.750 1.1688 0.05262 0.04273 -0.0514 0.3913 1.0000
9.000 1.1065 0.05649 0.04675 -0.0389 0.3888 1.0000
9.250 0.9825 0.06619 0.05655 -0.0246 0.3900 1.0000
9.500 0.8014 0.08975 0.07996 -0.0236 0.3923 1.0000
9.750 0.7590 0.09848 0.08867 -0.0246 0.3907 1.0000
10.000 0.7375 0.10488 0.09509 -0.0253 0.3904 1.0000
10.250 0.7230 0.11052 0.10077 -0.0260 0.3905 1.0000
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Polar data table (+)
Polar graphs
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