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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 50,000
Max Cl/Cd: 30.14 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe411-il-50000.txt
Download as CSV file: xf-goe411-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6232   0.10929   0.10231  -0.0355   1.0000   0.0973
 -12.000  -0.6194   0.10489   0.09793  -0.0356   1.0000   0.0953
 -11.750  -0.6354   0.09693   0.09003  -0.0395   1.0000   0.0918
 -11.500  -0.6819   0.08617   0.07931  -0.0468   1.0000   0.0890
 -11.250  -0.7293   0.07878   0.07191  -0.0507   1.0000   0.0876
 -11.000  -0.7717   0.07407   0.06704  -0.0507   1.0000   0.0868
 -10.750  -0.8119   0.07098   0.06376  -0.0473   1.0000   0.0861
 -10.500  -0.8476   0.06920   0.06174  -0.0417   1.0000   0.0853
 -10.250  -0.8500   0.06506   0.05747  -0.0394   1.0000   0.0840
 -10.000  -0.8558   0.06148   0.05373  -0.0365   1.0000   0.0828
  -9.750  -0.8632   0.05812   0.05014  -0.0330   1.0000   0.0817
  -9.500  -0.8686   0.05481   0.04653  -0.0294   1.0000   0.0805
  -9.250  -0.8701   0.05165   0.04302  -0.0259   1.0000   0.0792
  -9.000  -0.8672   0.04844   0.03941  -0.0225   1.0000   0.0783
  -8.750  -0.8577   0.04544   0.03594  -0.0198   1.0000   0.0778
  -8.500  -0.8423   0.04278   0.03294  -0.0177   1.0000   0.0792
  -8.250  -0.8217   0.04030   0.03014  -0.0163   1.0000   0.0817
  -8.000  -0.7923   0.03796   0.02745  -0.0158   1.0000   0.0842
  -7.750  -0.7512   0.03538   0.02487  -0.0169   1.0000   0.0876
  -7.500  -0.7320   0.03371   0.02321  -0.0150   1.0000   0.0917
  -7.250  -0.7203   0.03231   0.02169  -0.0120   1.0000   0.0965
  -7.000  -0.7153   0.03084   0.02030  -0.0083   1.0000   0.1029
  -6.750  -0.7113   0.02938   0.01900  -0.0044   1.0000   0.1161
  -6.500  -0.7087   0.02778   0.01770  -0.0004   1.0000   0.1466
  -6.250  -0.7142   0.02572   0.01647   0.0049   1.0000   0.2403
  -6.000  -0.7213   0.02453   0.01602   0.0111   1.0000   0.3514
  -5.750  -0.7238   0.02415   0.01589   0.0173   1.0000   0.4224
  -5.500  -0.7254   0.02408   0.01596   0.0236   1.0000   0.4780
  -5.250  -0.7196   0.02401   0.01589   0.0285   1.0000   0.5189
  -5.000  -0.7128   0.02414   0.01610   0.0337   1.0000   0.5641
  -4.750  -0.6991   0.02402   0.01592   0.0374   1.0000   0.6000
  -4.500  -0.6840   0.02431   0.01627   0.0417   1.0000   0.6441
  -4.250  -0.6563   0.02583   0.01788   0.0460   1.0000   0.6968
  -4.000  -0.6230   0.02671   0.01861   0.0477   1.0000   0.7330
  -3.750  -0.5867   0.02723   0.01889   0.0478   1.0000   0.7614
  -3.500  -0.5460   0.02784   0.01921   0.0470   1.0000   0.7886
  -3.250  -0.5011   0.02850   0.01960   0.0453   1.0000   0.8151
  -3.000  -0.4105   0.03004   0.02072   0.0362   1.0000   0.8388
  -2.750  -0.3311   0.03088   0.02119   0.0281   1.0000   0.8633
  -2.500  -0.2772   0.03102   0.02112   0.0233   1.0000   0.8874
  -2.250  -0.2154   0.03093   0.02081   0.0165   1.0000   0.9088
  -2.000  -0.1653   0.03059   0.02033   0.0112   1.0000   0.9301
  -1.750  -0.1084   0.03005   0.01966   0.0043   1.0000   0.9501
  -1.500  -0.0542   0.02942   0.01894  -0.0026   1.0000   0.9707
  -1.250   0.0116   0.02845   0.01790  -0.0121   1.0000   0.9907
  -1.000   0.0434   0.02773   0.01714  -0.0157   1.0000   1.0000
  -0.750   0.0368   0.02737   0.01682  -0.0123   1.0000   1.0000
  -0.500   0.0269   0.02707   0.01656  -0.0085   1.0000   1.0000
  -0.250   0.0142   0.02688   0.01638  -0.0044   1.0000   1.0000
   0.000   0.0000   0.02681   0.01632   0.0000   1.0000   1.0000
   0.250  -0.0142   0.02688   0.01638   0.0044   1.0000   1.0000
   0.500  -0.0269   0.02707   0.01656   0.0086   1.0000   1.0000
   0.750  -0.0368   0.02736   0.01682   0.0124   1.0000   1.0000
   1.000  -0.0434   0.02772   0.01714   0.0157   1.0000   1.0000
   1.250  -0.0119   0.02845   0.01789   0.0121   0.9907   1.0000
   1.500   0.0537   0.02941   0.01892   0.0027   0.9708   1.0000
   1.750   0.1083   0.03005   0.01966  -0.0043   0.9502   1.0000
   2.000   0.1654   0.03058   0.02032  -0.0112   0.9301   1.0000
   2.250   0.2153   0.03093   0.02080  -0.0165   0.9089   1.0000
   2.500   0.2765   0.03103   0.02113  -0.0232   0.8875   1.0000
   2.750   0.3316   0.03086   0.02118  -0.0282   0.8632   1.0000
   3.000   0.4105   0.03003   0.02071  -0.0362   0.8389   1.0000
   3.250   0.5010   0.02850   0.01961  -0.0453   0.8151   1.0000
   3.500   0.5460   0.02783   0.01920  -0.0470   0.7886   1.0000
   3.750   0.5869   0.02722   0.01888  -0.0478   0.7613   1.0000
   4.000   0.6233   0.02670   0.01860  -0.0477   0.7329   1.0000
   4.250   0.6560   0.02575   0.01780  -0.0458   0.6954   1.0000
   4.500   0.6842   0.02431   0.01628  -0.0417   0.6442   1.0000
   4.750   0.6987   0.02401   0.01590  -0.0373   0.5996   1.0000
   5.000   0.7127   0.02413   0.01608  -0.0337   0.5635   1.0000
   5.250   0.7200   0.02403   0.01592  -0.0286   0.5197   1.0000
   5.500   0.7251   0.02406   0.01594  -0.0235   0.4772   1.0000
   5.750   0.7235   0.02415   0.01588  -0.0172   0.4216   1.0000
   6.000   0.7209   0.02453   0.01601  -0.0110   0.3496   1.0000
   6.250   0.7139   0.02573   0.01648  -0.0048   0.2387   1.0000
   6.500   0.7088   0.02775   0.01769   0.0003   0.1481   1.0000
   6.750   0.7115   0.02937   0.01900   0.0044   0.1166   1.0000
   7.000   0.7155   0.03083   0.02030   0.0083   0.1033   1.0000
   7.250   0.7204   0.03230   0.02167   0.0120   0.0966   1.0000
   7.500   0.7320   0.03372   0.02321   0.0150   0.0916   1.0000
   7.750   0.7515   0.03542   0.02490   0.0168   0.0874   1.0000
   8.000   0.7923   0.03794   0.02743   0.0157   0.0843   1.0000
   8.250   0.8208   0.04026   0.03010   0.0164   0.0814   1.0000
   8.500   0.8424   0.04278   0.03295   0.0177   0.0792   1.0000
   8.750   0.8577   0.04546   0.03594   0.0198   0.0776   1.0000
   9.000   0.8672   0.04844   0.03940   0.0225   0.0782   1.0000
   9.250   0.8706   0.05157   0.04293   0.0258   0.0794   1.0000
   9.500   0.8682   0.05483   0.04656   0.0295   0.0804   1.0000
   9.750   0.8634   0.05808   0.05009   0.0330   0.0817   1.0000
  10.000   0.8563   0.06141   0.05365   0.0364   0.0828   1.0000
  10.250   0.8489   0.06514   0.05756   0.0396   0.0840   1.0000
  10.500   0.8485   0.06912   0.06166   0.0416   0.0852   1.0000
  10.750   0.8112   0.07098   0.06376   0.0474   0.0861   1.0000
  11.000   0.7728   0.07400   0.06697   0.0506   0.0868   1.0000
  11.250   0.7301   0.07879   0.07191   0.0507   0.0876   1.0000
  11.500   0.6832   0.08607   0.07921   0.0468   0.0890   1.0000
  11.750   0.6367   0.09687   0.08998   0.0394   0.0922   1.0000
  12.000   0.6194   0.10508   0.09813   0.0354   0.0952   1.0000
  12.250   0.6243   0.10933   0.10236   0.0355   0.0973   1.0000
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