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GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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