GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 50,000 Max Cl/Cd: 43.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe57-il-50000-n5.txt Download as CSV file: xf-goe57-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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 -0.3230 0.11238 0.10564 -0.0266 1.0000 0.0737
-8.000 -0.3284 0.11169 0.10509 -0.0277 1.0000 0.0741
-7.750 -0.3296 0.11066 0.10417 -0.0304 1.0000 0.0743
-7.500 -0.3164 0.10306 0.09659 -0.0257 1.0000 0.0762
-7.250 -0.3105 0.09957 0.09314 -0.0241 1.0000 0.0794
-7.000 -0.3093 0.09735 0.09101 -0.0239 1.0000 0.0830
-6.750 -0.3106 0.09592 0.08967 -0.0252 1.0000 0.0864
-6.500 -0.3110 0.09555 0.08939 -0.0295 1.0000 0.0882
-6.000 -0.3060 0.08870 0.08268 -0.0268 1.0000 0.0908
-5.750 -0.3031 0.08589 0.07991 -0.0253 1.0000 0.0934
-5.500 -0.2986 0.08348 0.07753 -0.0255 1.0000 0.0966
-5.250 -0.2869 0.08176 0.07578 -0.0304 1.0000 0.1016
-5.000 -0.2761 0.07878 0.07278 -0.0330 1.0000 0.1039
-4.750 -0.2743 0.07560 0.06967 -0.0294 1.0000 0.1083
-4.250 -0.2434 0.07010 0.06408 -0.0352 1.0000 0.1195
-4.000 -0.2317 0.06734 0.06131 -0.0352 1.0000 0.1243
-3.750 -0.1929 0.06387 0.05765 -0.0433 0.9961 0.1334
-3.500 -0.1477 0.06069 0.05422 -0.0516 0.9899 0.1468
-3.250 -0.1175 0.05711 0.05058 -0.0549 0.9842 0.1630
-3.000 -0.0845 0.05390 0.04729 -0.0587 0.9779 0.1799
-2.750 -0.0478 0.05097 0.04423 -0.0632 0.9713 0.1966
-2.250 0.0722 0.04329 0.03534 -0.0801 0.9593 0.0994
-2.000 0.1233 0.04035 0.03182 -0.0856 0.9533 0.0875
-1.750 0.1623 0.03822 0.02944 -0.0891 0.9455 0.0904
-1.500 0.2044 0.03635 0.02733 -0.0928 0.9386 0.0932
-1.250 0.2490 0.03462 0.02492 -0.0959 0.9295 0.0884
-1.000 0.2949 0.03273 0.02277 -0.0998 0.9227 0.0872
-0.750 0.3330 0.03132 0.02106 -0.1019 0.9119 0.0865
-0.500 0.3740 0.03000 0.01944 -0.1042 0.9025 0.0862
-0.250 0.4185 0.02874 0.01786 -0.1070 0.8943 0.0865
0.000 0.4546 0.02781 0.01666 -0.1082 0.8830 0.0875
0.250 0.4915 0.02692 0.01555 -0.1093 0.8722 0.0897
0.500 0.5293 0.02618 0.01472 -0.1106 0.8612 0.0984
0.750 0.5664 0.02537 0.01378 -0.1115 0.8491 0.1061
1.000 0.5995 0.02463 0.01296 -0.1115 0.8345 0.1116
1.250 0.6297 0.02400 0.01226 -0.1110 0.8175 0.1185
1.500 0.6585 0.02345 0.01169 -0.1103 0.7988 0.1310
1.750 0.6881 0.02285 0.01121 -0.1097 0.7792 0.1597
2.000 0.7181 0.02203 0.01067 -0.1092 0.7591 0.2248
2.250 0.7393 0.02046 0.01028 -0.1069 0.7358 1.0000
2.500 0.7653 0.02039 0.00994 -0.1055 0.7100 1.0000
2.750 0.7918 0.02033 0.00967 -0.1043 0.6832 1.0000
3.000 0.8188 0.02033 0.00950 -0.1032 0.6579 1.0000
3.250 0.8444 0.02048 0.00951 -0.1022 0.6327 1.0000
3.500 0.8700 0.02068 0.00957 -0.1011 0.6072 1.0000
3.750 0.8947 0.02095 0.00973 -0.1000 0.5798 1.0000
4.000 0.9185 0.02129 0.00995 -0.0989 0.5502 1.0000
4.250 0.9415 0.02169 0.01024 -0.0976 0.5190 1.0000
4.500 0.9640 0.02216 0.01057 -0.0964 0.4873 1.0000
4.750 0.9860 0.02270 0.01099 -0.0951 0.4566 1.0000
5.000 1.0076 0.02333 0.01147 -0.0938 0.4281 1.0000
5.250 1.0291 0.02404 0.01204 -0.0927 0.4026 1.0000
5.500 1.0509 0.02478 0.01272 -0.0916 0.3803 1.0000
5.750 1.0731 0.02557 0.01348 -0.0907 0.3622 1.0000
6.000 1.0961 0.02636 0.01428 -0.0899 0.3471 1.0000
6.250 1.1198 0.02716 0.01514 -0.0893 0.3342 1.0000
6.500 1.1443 0.02798 0.01605 -0.0887 0.3239 1.0000
6.750 1.1688 0.02880 0.01695 -0.0882 0.3155 1.0000
7.000 1.1886 0.02954 0.01776 -0.0870 0.3006 1.0000
7.250 1.2030 0.03023 0.01853 -0.0852 0.2788 1.0000
7.500 1.2201 0.03097 0.01936 -0.0838 0.2631 1.0000
7.750 1.2386 0.03174 0.02028 -0.0825 0.2511 1.0000
8.000 1.2560 0.03254 0.02130 -0.0811 0.2389 1.0000
8.250 1.2733 0.03337 0.02230 -0.0796 0.2285 1.0000
8.500 1.2855 0.03428 0.02336 -0.0777 0.2098 1.0000
8.750 1.2971 0.03530 0.02452 -0.0757 0.1926 1.0000
9.000 1.3036 0.03663 0.02586 -0.0734 0.1656 1.0000
9.250 1.3056 0.03838 0.02736 -0.0709 0.0799 1.0000
9.500 1.3038 0.04115 0.02986 -0.0682 0.0553 1.0000
9.750 1.3046 0.04377 0.03254 -0.0658 0.0458 1.0000
10.000 1.3047 0.04639 0.03532 -0.0637 0.0411 1.0000
10.250 1.3011 0.04941 0.03854 -0.0619 0.0383 1.0000
10.500 1.2975 0.05247 0.04179 -0.0605 0.0362 1.0000
10.750 1.2921 0.05588 0.04542 -0.0595 0.0347 1.0000
11.000 1.2845 0.05972 0.04948 -0.0591 0.0336 1.0000
11.250 1.2754 0.06401 0.05398 -0.0592 0.0329 1.0000
11.500 1.2651 0.06874 0.05892 -0.0599 0.0323 1.0000
11.750 1.2540 0.07386 0.06425 -0.0610 0.0320 1.0000
12.000 1.2429 0.07926 0.06985 -0.0625 0.0317 1.0000
12.250 1.2319 0.08478 0.07555 -0.0642 0.0315 1.0000
12.500 1.2218 0.09026 0.08118 -0.0660 0.0312 1.0000
12.750 1.2128 0.09554 0.08660 -0.0675 0.0310 1.0000
13.000 1.2054 0.10051 0.09168 -0.0689 0.0307 1.0000
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Polar data table (+)
Polar graphs
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