GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 500,000 Max Cl/Cd: 104.36 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe174-il-500000.txt Download as CSV file: xf-goe174-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 174 (ALBATROS 5020) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2957 0.10140 0.09918 -0.0261 1.0000 0.0185
-8.500 -0.2976 0.09891 0.09672 -0.0276 1.0000 0.0186
-8.250 -0.3003 0.09640 0.09426 -0.0281 1.0000 0.0186
-8.000 -0.2238 0.08010 0.07820 -0.0301 0.9993 0.0190
-7.750 -0.2072 0.07610 0.07420 -0.0322 0.9970 0.0193
-7.500 -0.1918 0.07204 0.07014 -0.0355 0.9939 0.0198
-7.250 -0.1780 0.06794 0.06604 -0.0392 0.9878 0.0203
-7.000 -0.1654 0.06376 0.06186 -0.0431 0.9774 0.0211
-6.750 -0.1515 0.05924 0.05733 -0.0480 0.9623 0.0220
-6.000 -0.1320 0.05943 0.05724 -0.0732 0.9565 0.0232
-5.750 -0.1013 0.05291 0.05064 -0.0806 0.9438 0.0236
-5.500 -0.0685 0.04989 0.04756 -0.0849 0.9286 0.0242
-5.250 -0.0324 0.04653 0.04405 -0.0904 0.9075 0.0251
-5.000 0.0001 0.04283 0.04015 -0.0952 0.8852 0.0267
-4.750 0.0465 0.03306 0.02982 -0.1049 0.8686 0.0295
-4.500 0.0678 0.03179 0.02847 -0.1051 0.8510 0.0302
-4.250 0.0918 0.03022 0.02677 -0.1057 0.8346 0.0311
-4.000 0.1188 0.02784 0.02416 -0.1067 0.8182 0.0329
-3.750 0.1515 0.02275 0.01832 -0.1087 0.8028 0.0374
-3.500 0.1756 0.02164 0.01719 -0.1087 0.7836 0.0387
-3.250 0.2014 0.02057 0.01592 -0.1087 0.7633 0.0411
-3.000 0.2299 0.01864 0.01342 -0.1089 0.7403 0.0473
-2.750 0.2551 0.01768 0.01239 -0.1087 0.7146 0.0495
-2.500 0.2817 0.01720 0.01165 -0.1084 0.6908 0.0542
-2.250 0.3079 0.01615 0.01037 -0.1085 0.6727 0.0615
-2.000 0.3361 0.01790 0.01192 -0.1077 0.6573 0.0699
-1.750 0.3615 0.01513 0.00905 -0.1083 0.6454 0.0786
-1.500 0.3885 0.01451 0.00830 -0.1084 0.6341 0.0912
-1.250 0.4200 0.01419 0.00751 -0.1073 0.6243 0.0698
-1.000 0.4497 0.01165 0.00456 -0.1066 0.6156 0.0442
-0.750 0.4775 0.01106 0.00390 -0.1064 0.6069 0.0430
-0.250 0.5327 0.01042 0.00313 -0.1059 0.5889 0.0426
0.000 0.5603 0.01022 0.00288 -0.1057 0.5798 0.0429
0.250 0.5879 0.01007 0.00268 -0.1056 0.5697 0.0433
0.500 0.6156 0.00995 0.00254 -0.1054 0.5588 0.0445
0.750 0.6432 0.00988 0.00241 -0.1052 0.5471 0.0453
1.000 0.6706 0.00983 0.00230 -0.1050 0.5342 0.0459
1.250 0.6980 0.00979 0.00220 -0.1048 0.5203 0.0481
1.500 0.7253 0.00980 0.00215 -0.1046 0.5045 0.0527
1.750 0.7524 0.00961 0.00223 -0.1045 0.4867 0.1855
2.000 0.7791 0.00951 0.00232 -0.1044 0.4679 0.2891
2.250 0.8024 0.00823 0.00248 -0.1037 0.4500 1.0000
2.500 0.8288 0.00845 0.00256 -0.1033 0.4321 1.0000
2.750 0.8552 0.00867 0.00266 -0.1030 0.4156 1.0000
3.000 0.8815 0.00890 0.00278 -0.1027 0.4004 1.0000
3.250 0.9076 0.00914 0.00292 -0.1024 0.3865 1.0000
3.500 0.9340 0.00936 0.00306 -0.1022 0.3744 1.0000
3.750 0.9604 0.00958 0.00322 -0.1019 0.3636 1.0000
4.000 0.9865 0.00981 0.00339 -0.1016 0.3542 1.0000
4.250 1.0128 0.01003 0.00356 -0.1013 0.3458 1.0000
4.500 1.0391 0.01024 0.00374 -0.1011 0.3382 1.0000
4.750 1.0653 0.01045 0.00394 -0.1008 0.3312 1.0000
5.000 1.0913 0.01068 0.00415 -0.1005 0.3249 1.0000
5.250 1.1176 0.01087 0.00434 -0.1003 0.3182 1.0000
5.500 1.1430 0.01115 0.00459 -0.0999 0.3124 1.0000
5.750 1.1696 0.01131 0.00479 -0.0997 0.3074 1.0000
6.000 1.1954 0.01153 0.00502 -0.0994 0.3016 1.0000
6.250 1.2210 0.01176 0.00524 -0.0991 0.2939 1.0000
6.500 1.2464 0.01198 0.00548 -0.0987 0.2851 1.0000
6.750 1.2721 0.01219 0.00570 -0.0984 0.2766 1.0000
7.000 1.2970 0.01246 0.00595 -0.0980 0.2663 1.0000
7.250 1.3220 0.01271 0.00621 -0.0976 0.2551 1.0000
7.500 1.3468 0.01298 0.00648 -0.0972 0.2432 1.0000
7.750 1.3709 0.01330 0.00679 -0.0967 0.2288 1.0000
8.000 1.3934 0.01377 0.00716 -0.0960 0.2054 1.0000
8.250 1.4106 0.01475 0.00784 -0.0946 0.1561 1.0000
8.500 1.4268 0.01580 0.00868 -0.0931 0.1227 1.0000
8.750 1.4441 0.01671 0.00948 -0.0916 0.0985 1.0000
9.000 1.4535 0.01830 0.01076 -0.0891 0.0508 1.0000
9.250 1.4691 0.01926 0.01174 -0.0873 0.0345 1.0000
9.500 1.4828 0.02032 0.01272 -0.0853 0.0229 1.0000
9.750 1.4977 0.02120 0.01364 -0.0835 0.0201 1.0000
10.000 1.5085 0.02231 0.01483 -0.0810 0.0180 1.0000
10.250 1.5194 0.02319 0.01582 -0.0785 0.0173 1.0000
10.500 1.5274 0.02421 0.01694 -0.0757 0.0165 1.0000
10.750 1.5337 0.02537 0.01821 -0.0729 0.0158 1.0000
11.000 1.5377 0.02674 0.01969 -0.0700 0.0151 1.0000
11.250 1.5369 0.02856 0.02161 -0.0671 0.0144 1.0000
11.500 1.5304 0.03105 0.02424 -0.0643 0.0139 1.0000
11.750 1.5249 0.03374 0.02708 -0.0623 0.0136 1.0000
12.000 1.5264 0.03602 0.02949 -0.0611 0.0133 1.0000
12.250 1.5252 0.03872 0.03231 -0.0602 0.0131 1.0000
12.500 1.5225 0.04179 0.03550 -0.0596 0.0128 1.0000
12.750 1.5182 0.04521 0.03905 -0.0593 0.0126 1.0000
13.000 1.5132 0.04891 0.04289 -0.0594 0.0124 1.0000
13.250 1.5073 0.05281 0.04690 -0.0596 0.0122 1.0000
13.500 1.5007 0.05683 0.05104 -0.0599 0.0120 1.0000
13.750 1.4935 0.06094 0.05527 -0.0602 0.0118 1.0000
14.000 1.4860 0.06510 0.05954 -0.0606 0.0117 1.0000
14.250 1.4786 0.06930 0.06383 -0.0610 0.0115 1.0000
14.500 1.4717 0.07352 0.06814 -0.0615 0.0114 1.0000
14.750 1.4651 0.07770 0.07242 -0.0620 0.0112 1.0000
15.000 1.4592 0.08182 0.07661 -0.0626 0.0110 1.0000
15.250 1.4539 0.08582 0.08068 -0.0630 0.0108 1.0000
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Polar data table (+)
Polar graphs
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