GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 100,000 Max Cl/Cd: 34.21 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe504-il-100000.txt Download as CSV file: xf-goe504-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1220 0.10199 0.09770 -0.0818 0.9416 0.1727
-9.000 -0.1467 0.09861 0.09440 -0.0864 0.9300 0.1801
-8.750 -0.3716 0.06869 0.06409 -0.1023 0.9021 0.0927
-8.500 -0.3299 0.06445 0.05999 -0.1043 0.8989 0.0877
-8.250 -0.4140 0.05708 0.05152 -0.0984 0.8825 0.0797
-8.000 -0.3925 0.05234 0.04650 -0.1000 0.8787 0.0781
-7.750 -0.3991 0.05022 0.04417 -0.0960 0.8674 0.0775
-7.500 -0.3797 0.04670 0.04007 -0.0965 0.8631 0.0781
-7.250 -0.3831 0.04529 0.03838 -0.0922 0.8521 0.0782
-7.000 -0.3555 0.04246 0.03502 -0.0929 0.8481 0.0786
-6.750 -0.3534 0.04130 0.03358 -0.0890 0.8377 0.0787
-6.500 -0.3220 0.03922 0.03103 -0.0897 0.8335 0.0793
-6.250 -0.3080 0.03753 0.02927 -0.0879 0.8256 0.0809
-6.000 -0.2796 0.03610 0.02778 -0.0881 0.8197 0.0839
-5.750 -0.2367 0.03438 0.02585 -0.0903 0.8168 0.0867
-5.500 -0.2310 0.03413 0.02551 -0.0868 0.8066 0.0881
-5.250 -0.1921 0.03293 0.02408 -0.0881 0.8026 0.0918
-5.000 -0.1471 0.03111 0.02241 -0.0908 0.8006 0.0985
-4.500 -0.1105 0.03001 0.02126 -0.0874 0.7859 0.1093
-4.250 -0.1083 0.03011 0.02136 -0.0833 0.7757 0.1159
-4.000 -0.0788 0.02875 0.02027 -0.0833 0.7714 0.1468
-3.750 -0.0398 0.02800 0.02000 -0.0846 0.7689 0.3060
-3.500 -0.0483 0.02898 0.02096 -0.0789 0.7567 0.3211
-3.250 -0.0056 0.02857 0.02041 -0.0807 0.7540 0.3562
-3.000 -0.0091 0.02946 0.02133 -0.0759 0.7429 0.3693
-2.750 0.0291 0.02902 0.02080 -0.0771 0.7394 0.3938
-2.500 0.0776 0.02831 0.02006 -0.0800 0.7374 0.4210
-2.250 0.0654 0.02940 0.02115 -0.0739 0.7251 0.4288
-2.000 0.1107 0.02866 0.02041 -0.0763 0.7226 0.4540
-1.750 0.1612 0.02780 0.01958 -0.0794 0.7209 0.4865
-1.500 0.1421 0.02910 0.02089 -0.0723 0.7080 0.4955
-1.250 0.1929 0.02813 0.01997 -0.0755 0.7060 0.5250
-1.000 0.1774 0.02945 0.02138 -0.0691 0.6940 0.5358
-0.750 0.2252 0.02847 0.02049 -0.0718 0.6913 0.5697
-0.500 0.2838 0.02720 0.01948 -0.0762 0.6897 0.6333
-0.250 0.4470 0.02531 0.01833 -0.0984 0.6899 0.9270
0.000 0.5949 0.02436 0.01693 -0.1196 0.6880 0.9840
0.250 0.6326 0.02499 0.01747 -0.1231 0.6782 1.0000
0.500 0.6629 0.02466 0.01694 -0.1236 0.6735 1.0000
0.750 0.6469 0.02567 0.01792 -0.1166 0.6641 1.0000
1.000 0.6750 0.02550 0.01759 -0.1166 0.6589 1.0000
1.250 0.6881 0.02582 0.01781 -0.1142 0.6525 1.0000
1.500 0.6906 0.02640 0.01833 -0.1101 0.6446 1.0000
1.750 0.7357 0.02585 0.01761 -0.1127 0.6408 1.0000
2.000 0.7094 0.02735 0.01914 -0.1041 0.6307 1.0000
2.250 0.7513 0.02687 0.01852 -0.1061 0.6264 1.0000
2.500 0.7412 0.02798 0.01961 -0.1001 0.6179 1.0000
2.750 0.7688 0.02793 0.01947 -0.0999 0.6122 1.0000
3.000 0.8224 0.02717 0.01856 -0.1038 0.6088 1.0000
3.250 0.7892 0.02897 0.02042 -0.0942 0.5983 1.0000
3.500 0.8397 0.02825 0.01958 -0.0975 0.5944 1.0000
3.750 0.8165 0.02983 0.02119 -0.0895 0.5851 1.0000
4.000 0.8564 0.02942 0.02070 -0.0912 0.5803 1.0000
4.250 0.9186 0.02842 0.01956 -0.0965 0.5770 1.0000
4.500 0.8738 0.03064 0.02187 -0.0852 0.5663 1.0000
4.750 0.9330 0.02965 0.02078 -0.0898 0.5626 1.0000
5.000 0.8917 0.03180 0.02300 -0.0792 0.5528 1.0000
5.250 0.9466 0.03098 0.02210 -0.0833 0.5484 1.0000
5.500 1.0181 0.02976 0.02076 -0.0899 0.5451 1.0000
5.750 0.9510 0.03260 0.02373 -0.0754 0.5343 1.0000
6.000 1.0268 0.03120 0.02224 -0.0826 0.5308 1.0000
6.250 0.9589 0.03439 0.02554 -0.0687 0.5203 1.0000
6.500 1.0247 0.03300 0.02408 -0.0738 0.5165 1.0000
6.750 1.0876 0.03216 0.02318 -0.0792 0.5123 1.0000
7.000 1.0182 0.03542 0.02656 -0.0654 0.5022 1.0000
7.250 1.1025 0.03345 0.02451 -0.0731 0.4991 1.0000
7.500 1.0095 0.03851 0.02972 -0.0579 0.4872 1.0000
7.750 1.0868 0.03612 0.02729 -0.0635 0.4847 1.0000
8.000 0.7651 0.06465 0.05605 -0.0415 0.4401 1.0000
8.250 0.7987 0.06374 0.05514 -0.0411 0.4379 1.0000
8.500 0.8411 0.06172 0.05314 -0.0409 0.4369 1.0000
8.750 0.8878 0.05909 0.05051 -0.0407 0.4366 1.0000
9.000 0.9402 0.05600 0.04744 -0.0408 0.4365 1.0000
9.250 0.9994 0.05255 0.04402 -0.0416 0.4364 1.0000
9.500 1.0727 0.04842 0.03991 -0.0437 0.4364 1.0000
9.750 1.1608 0.04420 0.03568 -0.0480 0.4359 1.0000
10.000 0.7281 0.09365 0.08527 -0.0372 0.3831 1.0000
10.250 0.7247 0.09758 0.08925 -0.0373 0.3782 1.0000
10.500 0.7513 0.09776 0.08945 -0.0369 0.3756 1.0000
10.750 0.7914 0.09613 0.08786 -0.0362 0.3739 1.0000
11.000 0.7084 0.11032 0.10211 -0.0381 0.3646 1.0000
11.250 0.7129 0.11359 0.10542 -0.0385 0.3622 1.0000
11.500 0.7541 0.11203 0.10390 -0.0376 0.3593 1.0000
11.750 0.6735 0.13430 0.12634 -0.0447 0.4040 1.0000
12.000 0.6304 0.13824 0.13031 -0.0451 0.4009 1.0000
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Polar data table (+)
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