GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 50,000 Max Cl/Cd: 39.84 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe257-il-50000-n5.txt Download as CSV file: xf-goe257-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3900 0.10657 0.10000 -0.0182 1.0000 0.0961
-8.000 -0.3968 0.10484 0.09840 -0.0217 1.0000 0.0990
-7.750 -0.3992 0.10301 0.09664 -0.0297 1.0000 0.1001
-7.500 -0.3838 0.09691 0.09058 -0.0233 1.0000 0.1037
-7.250 -0.3767 0.09357 0.08728 -0.0243 1.0000 0.1089
-7.000 -0.3748 0.09150 0.08523 -0.0341 1.0000 0.1143
-6.750 -0.3650 0.08671 0.08050 -0.0289 1.0000 0.1196
-6.500 -0.3573 0.08451 0.07823 -0.0380 1.0000 0.1289
-6.000 -0.3379 0.07726 0.07104 -0.0402 1.0000 0.1442
-5.750 -0.3305 0.07329 0.06720 -0.0363 1.0000 0.1483
-5.500 -0.3186 0.07020 0.06406 -0.0397 1.0000 0.1603
-5.250 -0.3081 0.06734 0.06121 -0.0395 1.0000 0.1714
-4.750 -0.2924 0.06178 0.05574 -0.0385 1.0000 0.2068
-4.250 -0.2208 0.05186 0.04471 -0.0508 0.9996 0.0988
-4.000 -0.1763 0.04674 0.03916 -0.0561 0.9907 0.0816
-3.750 -0.1322 0.04306 0.03501 -0.0613 0.9812 0.0814
-3.500 -0.0880 0.03960 0.03106 -0.0659 0.9715 0.0784
-3.250 -0.0404 0.03635 0.02712 -0.0704 0.9620 0.0743
-3.000 0.0070 0.03396 0.02390 -0.0741 0.9513 0.0717
-2.750 0.0480 0.03174 0.02143 -0.0773 0.9394 0.0736
-2.500 0.0880 0.03007 0.01946 -0.0799 0.9269 0.0765
-2.250 0.1273 0.02853 0.01751 -0.0819 0.9145 0.0762
-2.000 0.1649 0.02723 0.01587 -0.0835 0.9022 0.0759
-1.750 0.2008 0.02614 0.01451 -0.0847 0.8903 0.0761
-1.500 0.2341 0.02526 0.01341 -0.0852 0.8776 0.0767
-1.250 0.2663 0.02456 0.01248 -0.0856 0.8644 0.0777
-1.000 0.2973 0.02397 0.01172 -0.0858 0.8511 0.0792
-0.750 0.3273 0.02353 0.01110 -0.0859 0.8381 0.0830
-0.500 0.3567 0.02311 0.01058 -0.0861 0.8254 0.0889
-0.250 0.3860 0.02277 0.01013 -0.0862 0.8131 0.0950
0.000 0.4154 0.02251 0.00973 -0.0861 0.8012 0.1008
0.250 0.4449 0.02221 0.00936 -0.0861 0.7902 0.1126
0.500 0.4680 0.02029 0.00936 -0.0857 0.7789 0.6183
1.000 0.5250 0.02007 0.00899 -0.0847 0.7555 1.0000
1.250 0.5528 0.02031 0.00899 -0.0844 0.7452 1.0000
1.500 0.5799 0.02061 0.00912 -0.0841 0.7338 1.0000
1.750 0.6067 0.02096 0.00934 -0.0839 0.7225 1.0000
2.000 0.6337 0.02131 0.00958 -0.0837 0.7119 1.0000
2.250 0.6616 0.02163 0.00979 -0.0835 0.7023 1.0000
2.500 0.6881 0.02207 0.01021 -0.0834 0.6907 1.0000
2.750 0.7147 0.02250 0.01061 -0.0833 0.6796 1.0000
3.000 0.7412 0.02288 0.01096 -0.0830 0.6682 1.0000
3.250 0.7675 0.02321 0.01127 -0.0825 0.6560 1.0000
3.500 0.7931 0.02350 0.01154 -0.0818 0.6420 1.0000
3.750 0.8180 0.02376 0.01181 -0.0810 0.6264 1.0000
4.000 0.8428 0.02402 0.01209 -0.0803 0.6107 1.0000
4.250 0.8682 0.02429 0.01242 -0.0797 0.5972 1.0000
4.500 0.8935 0.02466 0.01289 -0.0792 0.5845 1.0000
4.750 0.9184 0.02506 0.01340 -0.0788 0.5715 1.0000
5.000 0.9433 0.02543 0.01393 -0.0782 0.5585 1.0000
5.250 0.9681 0.02581 0.01445 -0.0777 0.5455 1.0000
5.500 0.9929 0.02618 0.01495 -0.0771 0.5321 1.0000
5.750 1.0174 0.02654 0.01547 -0.0765 0.5185 1.0000
6.000 1.0419 0.02692 0.01604 -0.0758 0.5046 1.0000
6.250 1.0661 0.02732 0.01661 -0.0751 0.4903 1.0000
6.500 1.0902 0.02774 0.01720 -0.0743 0.4755 1.0000
6.750 1.1139 0.02822 0.01786 -0.0735 0.4603 1.0000
7.000 1.1373 0.02874 0.01861 -0.0726 0.4444 1.0000
7.250 1.1596 0.02921 0.01924 -0.0715 0.4258 1.0000
7.500 1.1777 0.02956 0.01967 -0.0697 0.3971 1.0000
7.750 1.1929 0.02999 0.02013 -0.0676 0.3629 1.0000
8.000 1.2082 0.03069 0.02102 -0.0659 0.3315 1.0000
8.250 1.2174 0.03159 0.02187 -0.0634 0.2827 1.0000
8.500 1.2208 0.03322 0.02312 -0.0605 0.2318 1.0000
8.750 1.2209 0.03547 0.02517 -0.0577 0.1641 1.0000
9.000 1.2055 0.03910 0.02795 -0.0541 0.0822 1.0000
9.250 1.1932 0.04236 0.03100 -0.0506 0.0683 1.0000
9.500 1.1843 0.04565 0.03435 -0.0481 0.0606 1.0000
9.750 1.1760 0.04919 0.03796 -0.0464 0.0562 1.0000
10.000 1.1720 0.05252 0.04152 -0.0453 0.0525 1.0000
10.250 1.1673 0.05610 0.04529 -0.0446 0.0494 1.0000
10.500 1.1617 0.05990 0.04923 -0.0442 0.0469 1.0000
10.750 1.1544 0.06396 0.05338 -0.0439 0.0449 1.0000
11.000 1.1550 0.06716 0.05679 -0.0435 0.0423 1.0000
11.250 1.1547 0.07046 0.06029 -0.0431 0.0399 1.0000
11.500 1.1547 0.07373 0.06376 -0.0427 0.0381 1.0000
11.750 1.1561 0.07678 0.06690 -0.0419 0.0367 1.0000
12.000 1.1608 0.07933 0.06947 -0.0406 0.0355 1.0000
12.250 1.1722 0.08137 0.07180 -0.0388 0.0344 1.0000
12.500 1.1816 0.08389 0.07461 -0.0375 0.0331 1.0000
12.750 1.1865 0.08705 0.07803 -0.0370 0.0318 1.0000
13.000 1.1878 0.09070 0.08192 -0.0370 0.0307 1.0000
13.250 1.1866 0.09469 0.08611 -0.0375 0.0298 1.0000
13.500 1.1843 0.09891 0.09051 -0.0382 0.0292 1.0000
13.750 1.1807 0.10341 0.09520 -0.0392 0.0287 1.0000
14.000 1.1750 0.10842 0.10041 -0.0407 0.0284 1.0000
14.250 1.1661 0.11415 0.10637 -0.0430 0.0284 1.0000
14.500 1.1543 0.12069 0.11315 -0.0462 0.0284 1.0000
14.750 1.1397 0.12823 0.12092 -0.0506 0.0286 1.0000
15.000 1.1225 0.13709 0.13003 -0.0562 0.0289 1.0000
15.250 1.1031 0.14760 0.14076 -0.0631 0.0295 1.0000
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