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GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 500 AIRFOIL (goe500-il)
Reynolds number: 500,000
Max Cl/Cd: 120.62 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe500-il-500000-n5.txt
Download as CSV file: xf-goe500-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 500 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4746   0.02638   0.02301  -0.1558   0.9300   0.0157
 -10.750  -0.4546   0.02327   0.01957  -0.1597   0.9244   0.0164
 -10.500  -0.4312   0.02145   0.01753  -0.1618   0.9203   0.0170
 -10.250  -0.4052   0.02046   0.01643  -0.1629   0.9172   0.0177
 -10.000  -0.3801   0.01971   0.01556  -0.1635   0.9136   0.0185
  -9.750  -0.3548   0.01893   0.01464  -0.1640   0.9097   0.0195
  -9.500  -0.3290   0.01812   0.01364  -0.1645   0.9062   0.0205
  -9.250  -0.3027   0.01732   0.01269  -0.1651   0.9031   0.0214
  -9.000  -0.2760   0.01680   0.01209  -0.1655   0.9000   0.0223
  -8.750  -0.2497   0.01634   0.01157  -0.1656   0.8962   0.0232
  -8.500  -0.2230   0.01586   0.01096  -0.1658   0.8925   0.0242
  -8.250  -0.1958   0.01538   0.01035  -0.1660   0.8891   0.0253
  -8.000  -0.1682   0.01494   0.00975  -0.1663   0.8862   0.0261
  -7.750  -0.1420   0.01424   0.00894  -0.1664   0.8822   0.0270
  -7.500  -0.1152   0.01376   0.00841  -0.1666   0.8781   0.0281
  -7.250  -0.0877   0.01339   0.00795  -0.1667   0.8744   0.0291
  -7.000  -0.0599   0.01301   0.00748  -0.1668   0.8712   0.0301
  -6.750  -0.0327   0.01265   0.00703  -0.1669   0.8668   0.0312
  -6.500  -0.0053   0.01230   0.00659  -0.1669   0.8624   0.0321
  -6.250   0.0225   0.01196   0.00613  -0.1669   0.8584   0.0326
  -6.000   0.0501   0.01145   0.00554  -0.1670   0.8544   0.0338
  -5.750   0.0775   0.01106   0.00510  -0.1671   0.8491   0.0350
  -5.500   0.1053   0.01074   0.00472  -0.1671   0.8439   0.0360
  -5.250   0.1331   0.01046   0.00437  -0.1670   0.8383   0.0370
  -5.000   0.1606   0.01021   0.00405  -0.1669   0.8310   0.0382
  -4.750   0.1885   0.00999   0.00374  -0.1669   0.8240   0.0395
  -4.500   0.2161   0.00979   0.00348  -0.1667   0.8156   0.0407
  -4.250   0.2437   0.00953   0.00315  -0.1667   0.8067   0.0428
  -4.000   0.2714   0.00933   0.00289  -0.1665   0.7971   0.0454
  -3.750   0.2990   0.00917   0.00268  -0.1664   0.7875   0.0486
  -3.500   0.3268   0.00902   0.00247  -0.1663   0.7795   0.0537
  -3.250   0.3545   0.00887   0.00232  -0.1662   0.7711   0.0626
  -3.000   0.3821   0.00877   0.00224  -0.1661   0.7630   0.0773
  -2.750   0.4097   0.00872   0.00217  -0.1660   0.7539   0.0882
  -2.500   0.4373   0.00870   0.00210  -0.1658   0.7452   0.0960
  -2.250   0.4647   0.00869   0.00202  -0.1656   0.7368   0.1005
  -2.000   0.4924   0.00863   0.00196  -0.1655   0.7289   0.1058
  -1.500   0.5473   0.00863   0.00185  -0.1652   0.7128   0.1138
  -1.250   0.5745   0.00859   0.00181  -0.1650   0.7047   0.1230
  -1.000   0.6019   0.00857   0.00178  -0.1649   0.6961   0.1318
  -0.750   0.6290   0.00856   0.00176  -0.1647   0.6883   0.1394
  -0.500   0.6564   0.00854   0.00175  -0.1645   0.6803   0.1496
   0.000   0.7107   0.00845   0.00180  -0.1643   0.6646   0.2158
   0.250   0.7376   0.00846   0.00185  -0.1640   0.6566   0.2472
   0.500   0.7646   0.00848   0.00189  -0.1638   0.6476   0.2713
   0.750   0.7913   0.00851   0.00195  -0.1636   0.6388   0.2922
   1.000   0.8179   0.00856   0.00202  -0.1633   0.6295   0.3119
   1.250   0.8447   0.00860   0.00209  -0.1630   0.6207   0.3324
   1.500   0.8709   0.00866   0.00218  -0.1627   0.6116   0.3590
   1.750   0.8974   0.00869   0.00228  -0.1624   0.6019   0.3878
   2.000   0.9235   0.00874   0.00239  -0.1620   0.5922   0.4252
   2.250   0.9490   0.00880   0.00253  -0.1616   0.5813   0.4713
   2.500   0.9748   0.00885   0.00267  -0.1612   0.5699   0.5163
   2.750   1.0001   0.00893   0.00282  -0.1607   0.5579   0.5592
   3.250   1.0486   0.00909   0.00315  -0.1593   0.5285   0.6698
   3.750   1.0952   0.00908   0.00349  -0.1574   0.4909   1.0000
   4.000   1.1194   0.00932   0.00367  -0.1567   0.4771   1.0000
   4.250   1.1426   0.00961   0.00388  -0.1558   0.4606   1.0000
   4.500   1.1654   0.00992   0.00410  -0.1549   0.4439   1.0000
   4.750   1.1893   0.01017   0.00432  -0.1542   0.4317   1.0000
   5.000   1.2124   0.01046   0.00456  -0.1533   0.4178   1.0000
   5.250   1.2340   0.01081   0.00483  -0.1522   0.3990   1.0000
   5.500   1.2564   0.01112   0.00510  -0.1512   0.3833   1.0000
   5.750   1.2782   0.01145   0.00537  -0.1502   0.3663   1.0000
   6.000   1.2987   0.01184   0.00568  -0.1489   0.3413   1.0000
   6.250   1.3155   0.01243   0.00608  -0.1470   0.3026   1.0000
   6.500   1.3257   0.01341   0.00673  -0.1441   0.2455   1.0000
   6.750   1.3343   0.01437   0.00742  -0.1409   0.2000   1.0000
   7.000   1.3430   0.01532   0.00813  -0.1377   0.1553   1.0000
   7.250   1.3496   0.01640   0.00894  -0.1344   0.1113   1.0000
   7.500   1.3570   0.01745   0.00978  -0.1312   0.0751   1.0000
   7.750   1.3665   0.01839   0.01059  -0.1284   0.0533   1.0000
   8.000   1.3803   0.01909   0.01128  -0.1263   0.0458   1.0000
   8.250   1.3952   0.01973   0.01194  -0.1245   0.0417   1.0000
   8.500   1.4096   0.02041   0.01263  -0.1226   0.0385   1.0000
   8.750   1.4229   0.02118   0.01342  -0.1206   0.0356   1.0000
   9.000   1.4375   0.02187   0.01416  -0.1188   0.0338   1.0000
   9.250   1.4518   0.02259   0.01494  -0.1171   0.0319   1.0000
   9.500   1.4648   0.02342   0.01581  -0.1152   0.0300   1.0000
   9.750   1.4760   0.02439   0.01681  -0.1132   0.0280   1.0000
  10.000   1.4889   0.02526   0.01773  -0.1115   0.0265   1.0000
  10.250   1.5020   0.02614   0.01867  -0.1099   0.0250   1.0000
  10.500   1.5136   0.02713   0.01971  -0.1081   0.0232   1.0000
  10.750   1.5230   0.02833   0.02094  -0.1063   0.0214   1.0000
  11.000   1.5348   0.02938   0.02206  -0.1047   0.0201   1.0000
  11.250   1.5453   0.03054   0.02327  -0.1031   0.0185   1.0000
  11.500   1.5542   0.03187   0.02463  -0.1014   0.0171   1.0000
  11.750   1.5622   0.03332   0.02614  -0.0997   0.0161   1.0000
  12.000   1.5705   0.03478   0.02768  -0.0982   0.0151   1.0000
  12.250   1.5779   0.03635   0.02932  -0.0967   0.0142   1.0000
  12.500   1.5842   0.03809   0.03111  -0.0953   0.0133   1.0000
  12.750   1.5887   0.04006   0.03314  -0.0938   0.0125   1.0000
  13.000   1.5946   0.04195   0.03513  -0.0926   0.0120   1.0000
  13.250   1.5995   0.04399   0.03727  -0.0914   0.0114   1.0000
  13.500   1.6040   0.04616   0.03952  -0.0904   0.0109   1.0000
  13.750   1.6076   0.04850   0.04194  -0.0894   0.0105   1.0000
  14.000   1.6100   0.05105   0.04457  -0.0886   0.0101   1.0000
  14.250   1.6104   0.05391   0.04751  -0.0878   0.0097   1.0000
  14.500   1.6109   0.05685   0.05057  -0.0873   0.0095   1.0000
  14.750   1.6128   0.05969   0.05353  -0.0868   0.0092   1.0000
  15.000   1.6140   0.06270   0.05664  -0.0865   0.0089   1.0000
  15.250   1.6143   0.06589   0.05994  -0.0864   0.0086   1.0000
  15.500   1.6147   0.06914   0.06330  -0.0863   0.0083   1.0000
  15.750   1.6145   0.07257   0.06683  -0.0865   0.0081   1.0000
  16.000   1.6140   0.07610   0.07047  -0.0868   0.0078   1.0000
  16.250   1.6117   0.07998   0.07445  -0.0872   0.0077   1.0000
  16.500   1.6086   0.08407   0.07864  -0.0879   0.0075   1.0000
  16.750   1.6036   0.08855   0.08323  -0.0887   0.0073   1.0000
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