GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 50,000 Max Cl/Cd: 27.37 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe288-il-50000-n5.txt Download as CSV file: xf-goe288-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 288 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2567 0.11890 0.11184 -0.0480 1.0000 0.0865
-10.250 -0.2646 0.11717 0.11024 -0.0463 1.0000 0.0861
-10.000 -0.2622 0.11386 0.10698 -0.0479 0.9955 0.0857
-9.750 -0.2493 0.10859 0.10169 -0.0534 0.9860 0.0856
-9.500 -0.2411 0.10280 0.09590 -0.0594 0.9755 0.0861
-9.250 -0.2372 0.09633 0.08940 -0.0660 0.9644 0.0866
-9.000 -0.2306 0.09014 0.08322 -0.0723 0.9535 0.0872
-8.750 -0.2186 0.08559 0.07867 -0.0768 0.9406 0.0879
-8.500 -0.2242 0.07852 0.07158 -0.0829 0.9255 0.0881
-8.250 -0.2930 0.05742 0.04997 -0.1059 0.9025 0.0873
-8.000 -0.2827 0.05332 0.04566 -0.1097 0.8877 0.0884
-7.750 -0.2679 0.04970 0.04178 -0.1132 0.8746 0.0901
-7.500 -0.2452 0.04583 0.03752 -0.1176 0.8654 0.0932
-7.250 -0.2299 0.04214 0.03322 -0.1203 0.8518 0.0967
-7.000 -0.2024 0.04076 0.03182 -0.1214 0.8423 0.0999
-6.750 -0.1773 0.03904 0.02987 -0.1225 0.8318 0.1039
-6.500 -0.1514 0.03693 0.02735 -0.1239 0.8224 0.1089
-6.250 -0.1247 0.03602 0.02645 -0.1243 0.8129 0.1145
-6.000 -0.0975 0.03465 0.02482 -0.1252 0.8041 0.1228
-5.750 -0.0712 0.03369 0.02374 -0.1257 0.7948 0.1322
-5.500 -0.0421 0.03275 0.02275 -0.1264 0.7876 0.1441
-5.250 -0.0178 0.03212 0.02208 -0.1265 0.7781 0.1576
-5.000 0.0134 0.03139 0.02129 -0.1275 0.7719 0.1752
-4.750 0.0373 0.03117 0.02106 -0.1274 0.7625 0.1922
-4.500 0.0667 0.03087 0.02069 -0.1279 0.7556 0.2127
-4.250 0.0948 0.03078 0.02057 -0.1281 0.7487 0.2325
-4.000 0.1200 0.03086 0.02064 -0.1279 0.7407 0.2499
-3.750 0.1507 0.03072 0.02041 -0.1282 0.7351 0.2676
-3.500 0.1754 0.03085 0.02052 -0.1278 0.7274 0.2827
-3.250 0.2020 0.03092 0.02055 -0.1275 0.7204 0.2984
-3.000 0.2334 0.03076 0.02027 -0.1278 0.7153 0.3158
-2.750 0.2560 0.03103 0.02050 -0.1272 0.7075 0.3314
-2.500 0.2832 0.03107 0.02044 -0.1271 0.7008 0.3484
-2.250 0.3151 0.03091 0.02013 -0.1274 0.6959 0.3668
-2.000 0.3361 0.03123 0.02038 -0.1266 0.6868 0.3823
-1.750 0.3655 0.03109 0.02010 -0.1266 0.6797 0.3997
-1.500 0.3920 0.03110 0.01999 -0.1262 0.6715 0.4164
-1.250 0.4170 0.03112 0.01995 -0.1255 0.6627 0.4312
-1.000 0.4492 0.03081 0.01950 -0.1255 0.6566 0.4474
-0.750 0.4681 0.03119 0.01990 -0.1244 0.6465 0.4609
-0.500 0.4986 0.03102 0.01960 -0.1244 0.6402 0.4775
-0.250 0.5224 0.03127 0.01979 -0.1239 0.6322 0.4927
0.000 0.5472 0.03137 0.01986 -0.1232 0.6246 0.5057
0.250 0.5799 0.03110 0.01946 -0.1235 0.6192 0.5193
0.500 0.5987 0.03166 0.02001 -0.1226 0.6098 0.5310
0.750 0.6270 0.03158 0.01988 -0.1224 0.6031 0.5427
1.000 0.6538 0.03167 0.01991 -0.1222 0.5962 0.5550
1.250 0.6751 0.03204 0.02028 -0.1214 0.5873 0.5672
1.500 0.7068 0.03180 0.01997 -0.1215 0.5816 0.5814
1.750 0.7239 0.03240 0.02065 -0.1203 0.5721 0.5944
2.000 0.7512 0.03238 0.02062 -0.1200 0.5650 0.6110
2.250 0.7759 0.03250 0.02077 -0.1194 0.5577 0.6299
2.500 0.7944 0.03289 0.02130 -0.1181 0.5486 0.6512
2.750 0.8249 0.03249 0.02096 -0.1179 0.5431 0.6850
3.000 0.8330 0.03315 0.02198 -0.1151 0.5329 0.7331
3.250 0.8578 0.03273 0.02174 -0.1139 0.5262 1.0000
3.500 0.8768 0.03358 0.02247 -0.1132 0.5171 1.0000
3.750 0.9013 0.03405 0.02280 -0.1130 0.5093 1.0000
4.000 0.9307 0.03426 0.02283 -0.1131 0.5031 1.0000
4.250 0.9401 0.03557 0.02415 -0.1112 0.4931 1.0000
4.500 0.9727 0.03554 0.02393 -0.1116 0.4878 1.0000
4.750 0.9763 0.03719 0.02564 -0.1092 0.4778 1.0000
5.000 1.0026 0.03748 0.02581 -0.1088 0.4718 1.0000
5.250 1.0160 0.03858 0.02688 -0.1074 0.4645 1.0000
5.500 1.0256 0.03990 0.02822 -0.1056 0.4567 1.0000
5.750 1.0573 0.03991 0.02810 -0.1057 0.4526 1.0000
6.000 1.0405 0.04283 0.03114 -0.1016 0.4433 1.0000
6.250 1.0587 0.04363 0.03190 -0.1007 0.4380 1.0000
6.500 1.0950 0.04330 0.03146 -0.1011 0.4347 1.0000
6.750 1.0518 0.04869 0.03705 -0.0963 0.4236 1.0000
7.000 1.0774 0.04897 0.03727 -0.0959 0.4199 1.0000
7.250 1.1137 0.04847 0.03668 -0.0960 0.4175 1.0000
7.500 1.0429 0.05794 0.04642 -0.0927 0.4044 1.0000
7.750 1.0713 0.05787 0.04630 -0.0921 0.4021 1.0000
8.500 1.0495 0.07023 0.05881 -0.0905 0.3833 1.0000
9.500 0.9579 0.09841 0.08733 -0.0934 0.3536 1.0000
9.750 0.9741 0.10002 0.08894 -0.0931 0.3516 1.0000
10.000 0.9935 0.10118 0.09012 -0.0926 0.3502 1.0000
10.500 0.9447 0.11601 0.10511 -0.0956 0.3376 1.0000
10.750 0.9590 0.11791 0.10704 -0.0954 0.3353 1.0000
11.000 0.9747 0.11971 0.10887 -0.0952 0.3337 1.0000
11.250 0.9516 0.12712 0.11638 -0.0972 0.3293 1.0000
11.500 0.9432 0.13217 0.12149 -0.0985 0.3250 1.0000
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Polar data table (+)
Polar graphs
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