GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 50,000 Max Cl/Cd: 37.03 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe587-il-50000-n5.txt Download as CSV file: xf-goe587-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 587 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4434 0.09478 0.08823 -0.0166 1.0000 0.0729
-7.250 -0.4411 0.09190 0.08540 -0.0188 1.0000 0.0754
-7.000 -0.4394 0.09004 0.08357 -0.0238 1.0000 0.0778
-6.750 -0.4334 0.08808 0.08156 -0.0280 1.0000 0.0785
-6.500 -0.4252 0.08175 0.07538 -0.0235 1.0000 0.0821
-6.250 -0.4174 0.07857 0.07221 -0.0242 1.0000 0.0873
-6.000 -0.4065 0.07736 0.07082 -0.0298 1.0000 0.0918
-5.750 -0.4005 0.07187 0.06546 -0.0266 1.0000 0.0963
-5.500 -0.3873 0.06995 0.06336 -0.0296 1.0000 0.1054
-5.250 -0.3786 0.06547 0.05896 -0.0285 1.0000 0.1086
-5.000 -0.3669 0.06207 0.05555 -0.0281 1.0000 0.1128
-4.500 -0.3189 0.05309 0.04592 -0.0309 1.0000 0.0502
-4.250 -0.3044 0.04956 0.04229 -0.0303 1.0000 0.0467
-4.000 -0.2858 0.04605 0.03853 -0.0300 1.0000 0.0434
-3.750 -0.2611 0.04277 0.03465 -0.0294 1.0000 0.0397
-3.500 -0.2436 0.03972 0.03134 -0.0284 1.0000 0.0395
-3.250 -0.2270 0.03690 0.02835 -0.0274 1.0000 0.0415
-3.000 -0.2093 0.03476 0.02601 -0.0264 1.0000 0.0450
-2.750 -0.1885 0.03235 0.02314 -0.0252 1.0000 0.0461
-2.500 -0.1664 0.02994 0.02026 -0.0239 1.0000 0.0469
-2.250 -0.1437 0.02783 0.01767 -0.0227 1.0000 0.0490
-2.000 -0.1219 0.02620 0.01570 -0.0216 1.0000 0.0561
-1.750 -0.0984 0.02461 0.01371 -0.0206 1.0000 0.0616
-1.500 -0.0663 0.02321 0.01197 -0.0212 0.9963 0.0751
-1.250 -0.0224 0.02176 0.01005 -0.0236 0.9883 0.0934
-1.000 0.0174 0.02081 0.00893 -0.0261 0.9776 0.1216
-0.750 0.0545 0.01992 0.00796 -0.0281 0.9650 0.1495
-0.500 0.1194 0.01675 0.00713 -0.0350 0.9668 1.0000
-0.250 0.1601 0.01687 0.00673 -0.0378 0.9509 1.0000
0.000 0.2017 0.01696 0.00647 -0.0409 0.9359 1.0000
0.250 0.2440 0.01704 0.00626 -0.0440 0.9217 1.0000
0.500 0.2850 0.01710 0.00615 -0.0468 0.9071 1.0000
0.750 0.3241 0.01718 0.00610 -0.0492 0.8918 1.0000
1.000 0.3613 0.01726 0.00609 -0.0511 0.8760 1.0000
1.250 0.3969 0.01735 0.00613 -0.0526 0.8600 1.0000
1.500 0.4275 0.01750 0.00625 -0.0531 0.8423 1.0000
1.750 0.4567 0.01766 0.00644 -0.0533 0.8247 1.0000
2.000 0.4852 0.01783 0.00663 -0.0532 0.8077 1.0000
2.250 0.5129 0.01801 0.00685 -0.0530 0.7914 1.0000
2.500 0.5395 0.01821 0.00711 -0.0525 0.7754 1.0000
2.750 0.5638 0.01848 0.00753 -0.0516 0.7588 1.0000
3.000 0.5882 0.01876 0.00793 -0.0508 0.7429 1.0000
3.250 0.6123 0.01907 0.00839 -0.0499 0.7277 1.0000
3.500 0.6367 0.01940 0.00892 -0.0490 0.7127 1.0000
3.750 0.6607 0.01969 0.00948 -0.0479 0.6954 1.0000
4.000 0.6809 0.01963 0.00950 -0.0450 0.6616 1.0000
4.250 0.6986 0.01962 0.00959 -0.0418 0.6222 1.0000
4.500 0.7181 0.01974 0.00992 -0.0393 0.5883 1.0000
4.750 0.7344 0.01983 0.01013 -0.0358 0.5331 1.0000
5.000 0.7392 0.02042 0.01003 -0.0303 0.3527 1.0000
5.250 0.7377 0.02408 0.01173 -0.0269 0.0945 1.0000
5.500 0.7511 0.02604 0.01365 -0.0249 0.0684 1.0000
5.750 0.7634 0.02793 0.01566 -0.0226 0.0576 1.0000
6.000 0.7763 0.02967 0.01758 -0.0203 0.0489 1.0000
6.250 0.7906 0.03170 0.01976 -0.0180 0.0440 1.0000
6.500 0.8131 0.03367 0.02192 -0.0163 0.0395 1.0000
6.750 0.8401 0.03640 0.02481 -0.0155 0.0347 1.0000
7.000 0.8690 0.03915 0.02793 -0.0146 0.0332 1.0000
7.250 0.8932 0.04227 0.03150 -0.0133 0.0321 1.0000
7.500 0.9116 0.04526 0.03494 -0.0118 0.0305 1.0000
7.750 0.9262 0.04849 0.03850 -0.0104 0.0284 1.0000
8.000 0.9389 0.05260 0.04279 -0.0093 0.0271 1.0000
8.250 0.9483 0.05632 0.04695 -0.0076 0.0270 1.0000
8.500 0.9537 0.05973 0.05083 -0.0055 0.0273 1.0000
8.750 0.9536 0.06305 0.05468 -0.0031 0.0278 1.0000
9.000 0.9495 0.06667 0.05874 -0.0011 0.0284 1.0000
9.250 0.9419 0.07041 0.06281 0.0006 0.0289 1.0000
9.500 0.9298 0.07401 0.06667 0.0021 0.0294 1.0000
9.750 0.9134 0.07768 0.07052 0.0032 0.0298 1.0000
10.000 0.8968 0.08173 0.07472 0.0028 0.0301 1.0000
10.250 0.8798 0.08651 0.07961 0.0008 0.0305 1.0000
10.500 0.8643 0.09190 0.08507 -0.0023 0.0308 1.0000
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Polar data table (+)
Polar graphs
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