GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 500,000 Max Cl/Cd: 88.77 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe400-il-500000-n5.txt Download as CSV file: xf-goe400-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4329 0.10339 0.10119 0.0024 1.0000 0.0103
-8.750 -0.4308 0.09877 0.09659 0.0000 1.0000 0.0108
-8.500 -0.4320 0.09326 0.09110 -0.0030 1.0000 0.0113
-8.250 -0.4222 0.09105 0.08891 -0.0044 1.0000 0.0116
-8.000 -0.4122 0.08884 0.08671 -0.0059 1.0000 0.0120
-7.750 -0.4023 0.08635 0.08425 -0.0077 1.0000 0.0124
-7.500 -0.3912 0.08292 0.08083 -0.0111 1.0000 0.0130
-7.250 -0.3797 0.07822 0.07613 -0.0162 1.0000 0.0138
-7.000 -0.3590 0.06895 0.06682 -0.0289 0.9682 0.0153
-6.750 -0.3326 0.06677 0.06458 -0.0329 0.9368 0.0158
-6.500 -0.3125 0.06469 0.06240 -0.0352 0.8984 0.0164
-6.250 -0.2922 0.06133 0.05888 -0.0390 0.8599 0.0174
-6.000 -0.2576 0.04897 0.04621 -0.0548 0.8316 0.0204
-5.750 -0.2336 0.04744 0.04451 -0.0566 0.8023 0.0209
-5.500 -0.2081 0.04569 0.04261 -0.0586 0.7786 0.0215
-5.250 -0.1803 0.04300 0.03975 -0.0617 0.7593 0.0223
-4.750 -0.1035 0.01883 0.01396 -0.0801 0.7368 0.0269
-4.250 -0.0496 0.01437 0.00854 -0.0812 0.7117 0.0283
-4.000 -0.0223 0.01349 0.00743 -0.0812 0.7006 0.0287
-3.750 0.0052 0.01283 0.00657 -0.0811 0.6901 0.0291
-3.500 0.0327 0.01227 0.00583 -0.0810 0.6799 0.0295
-3.250 0.0605 0.01178 0.00519 -0.0808 0.6702 0.0299
-3.000 0.0881 0.01142 0.00470 -0.0807 0.6610 0.0305
-2.750 0.1159 0.01108 0.00426 -0.0805 0.6516 0.0312
-2.500 0.1437 0.01073 0.00379 -0.0804 0.6428 0.0317
-2.250 0.1715 0.01043 0.00338 -0.0802 0.6338 0.0322
-2.000 0.1994 0.01016 0.00303 -0.0800 0.6253 0.0328
-1.750 0.2272 0.00994 0.00273 -0.0798 0.6170 0.0336
-1.500 0.2552 0.00975 0.00248 -0.0797 0.6087 0.0343
-1.250 0.2830 0.00961 0.00226 -0.0795 0.6007 0.0351
-1.000 0.3110 0.00948 0.00208 -0.0793 0.5924 0.0357
-0.750 0.3388 0.00938 0.00193 -0.0791 0.5846 0.0363
-0.500 0.3668 0.00929 0.00180 -0.0790 0.5762 0.0369
-0.250 0.3947 0.00920 0.00165 -0.0788 0.5682 0.0388
0.000 0.4225 0.00911 0.00155 -0.0786 0.5597 0.0420
0.250 0.4504 0.00903 0.00147 -0.0785 0.5515 0.0480
0.500 0.4780 0.00900 0.00155 -0.0783 0.5428 0.0822
0.750 0.5060 0.00907 0.00160 -0.0782 0.5337 0.0912
1.000 0.5337 0.00914 0.00163 -0.0780 0.5224 0.0958
1.250 0.5612 0.00919 0.00165 -0.0778 0.5072 0.0995
1.500 0.5887 0.00927 0.00168 -0.0776 0.4907 0.1031
1.750 0.6162 0.00935 0.00172 -0.0775 0.4774 0.1059
2.000 0.6437 0.00943 0.00176 -0.0773 0.4654 0.1073
2.250 0.6711 0.00945 0.00176 -0.0771 0.4510 0.1114
2.500 0.6984 0.00954 0.00183 -0.0770 0.4349 0.1155
2.750 0.7256 0.00963 0.00189 -0.0768 0.4193 0.1175
3.000 0.7529 0.00973 0.00196 -0.0766 0.4054 0.1185
3.250 0.7801 0.00984 0.00205 -0.0765 0.3915 0.1196
3.750 0.8345 0.01008 0.00225 -0.0761 0.3659 0.1218
4.000 0.8616 0.01020 0.00238 -0.0759 0.3533 0.1241
4.250 0.8885 0.01035 0.00253 -0.0758 0.3398 0.1268
4.500 0.9153 0.01054 0.00270 -0.0756 0.3236 0.1303
4.750 0.9419 0.01074 0.00288 -0.0754 0.3072 0.1352
5.000 0.9685 0.01091 0.00311 -0.0752 0.2933 0.1547
6.500 1.1150 0.01265 0.00543 -0.0730 0.1011 1.0000
6.750 1.1393 0.01318 0.00590 -0.0726 0.0870 1.0000
7.000 1.1640 0.01364 0.00634 -0.0722 0.0783 1.0000
7.250 1.1891 0.01400 0.00673 -0.0718 0.0711 1.0000
7.500 1.2132 0.01451 0.00719 -0.0714 0.0554 1.0000
7.750 1.2329 0.01566 0.00807 -0.0706 0.0217 1.0000
8.000 1.2560 0.01627 0.00871 -0.0700 0.0171 1.0000
8.250 1.2787 0.01691 0.00939 -0.0693 0.0144 1.0000
8.500 1.3015 0.01751 0.01006 -0.0687 0.0130 1.0000
8.750 1.3240 0.01809 0.01071 -0.0680 0.0119 1.0000
9.000 1.3457 0.01876 0.01144 -0.0673 0.0108 1.0000
9.250 1.3657 0.01962 0.01237 -0.0664 0.0099 1.0000
9.500 1.3851 0.02049 0.01333 -0.0655 0.0093 1.0000
9.750 1.4049 0.02126 0.01420 -0.0645 0.0089 1.0000
10.000 1.4234 0.02212 0.01514 -0.0635 0.0084 1.0000
10.250 1.4411 0.02300 0.01611 -0.0624 0.0079 1.0000
10.500 1.4579 0.02391 0.01709 -0.0612 0.0075 1.0000
10.750 1.4727 0.02494 0.01818 -0.0599 0.0071 1.0000
11.000 1.4820 0.02638 0.01974 -0.0580 0.0067 1.0000
11.250 1.4900 0.02764 0.02110 -0.0559 0.0065 1.0000
11.500 1.4969 0.02896 0.02253 -0.0539 0.0064 1.0000
11.750 1.5017 0.03054 0.02424 -0.0521 0.0062 1.0000
12.000 1.5054 0.03239 0.02621 -0.0507 0.0061 1.0000
12.250 1.5083 0.03450 0.02845 -0.0497 0.0059 1.0000
12.500 1.5106 0.03688 0.03095 -0.0491 0.0058 1.0000
12.750 1.5118 0.03954 0.03374 -0.0488 0.0056 1.0000
13.000 1.5122 0.04242 0.03674 -0.0488 0.0055 1.0000
13.250 1.5116 0.04552 0.03996 -0.0490 0.0054 1.0000
13.500 1.5099 0.04881 0.04337 -0.0493 0.0053 1.0000
13.750 1.5069 0.05233 0.04703 -0.0497 0.0052 1.0000
14.000 1.5028 0.05605 0.05087 -0.0503 0.0051 1.0000
14.250 1.4972 0.06003 0.05497 -0.0510 0.0051 1.0000
14.500 1.4908 0.06421 0.05927 -0.0519 0.0050 1.0000
14.750 1.4830 0.06863 0.06380 -0.0529 0.0049 1.0000
15.000 1.4742 0.07331 0.06860 -0.0541 0.0049 1.0000
15.250 1.4650 0.07822 0.07363 -0.0555 0.0048 1.0000
15.500 1.4549 0.08343 0.07896 -0.0572 0.0048 1.0000
15.750 1.4443 0.08887 0.08452 -0.0590 0.0047 1.0000
16.000 1.4330 0.09455 0.09032 -0.0610 0.0047 1.0000
16.250 1.4206 0.10050 0.09640 -0.0632 0.0046 1.0000
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Polar data table (+)
Polar graphs
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