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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 50,000
Max Cl/Cd: 29.77 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe385-il-50000.txt
Download as CSV file: xf-goe385-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3699   0.11029   0.10369  -0.0188   1.0000   0.1716
  -8.500  -0.3627   0.10638   0.09984  -0.0189   1.0000   0.1780
  -8.250  -0.3650   0.10433   0.09786  -0.0201   1.0000   0.1871
  -8.000  -0.3555   0.10029   0.09388  -0.0196   1.0000   0.1947
  -7.750  -0.3668   0.09900   0.09273  -0.0210   1.0000   0.2030
  -7.500  -0.3529   0.09474   0.08850  -0.0196   1.0000   0.2138
  -7.250  -0.3778   0.09458   0.08854  -0.0242   1.0000   0.2196
  -7.000  -0.3661   0.09059   0.08461  -0.0213   1.0000   0.2339
  -6.750  -0.3595   0.08725   0.08135  -0.0193   1.0000   0.2477
  -6.500  -0.3599   0.08464   0.07885  -0.0178   1.0000   0.2627
  -6.250  -0.3650   0.08252   0.07685  -0.0165   1.0000   0.2790
  -6.000  -0.3747   0.08087   0.07531  -0.0156   1.0000   0.2957
  -5.750  -0.3652   0.07753   0.07207  -0.0098   1.0000   0.3197
  -5.500  -0.3791   0.07634   0.07100  -0.0078   1.0000   0.3410
  -5.250  -0.3766   0.07375   0.06849  -0.0022   1.0000   0.3666
  -5.000  -0.3832   0.07193   0.06679   0.0024   1.0000   0.3943
  -4.750   0.0572   0.04419   0.03771  -0.0292   1.0000   1.0000
  -4.500   0.0682   0.04232   0.03591  -0.0303   1.0000   1.0000
  -4.250   0.0785   0.04056   0.03423  -0.0312   1.0000   1.0000
  -4.000   0.0187   0.04324   0.03719  -0.0163   1.0000   0.9625
  -3.750  -0.0431   0.04556   0.03982  -0.0027   1.0000   0.9213
  -3.500  -0.1008   0.04734   0.04189   0.0092   1.0000   0.8946
  -3.250  -0.1528   0.04845   0.04324   0.0190   1.0000   0.8682
  -3.000  -0.2058   0.04945   0.04446   0.0287   1.0000   0.8515
  -2.750  -0.2567   0.04995   0.04518   0.0378   1.0000   0.8359
  -2.250  -0.1644   0.04055   0.03264  -0.0419   1.0000   0.2166
  -2.000  -0.1123   0.03857   0.02975  -0.0467   0.9948   0.1881
  -1.750  -0.0578   0.03663   0.02719  -0.0518   0.9856   0.1713
  -1.500  -0.0069   0.03519   0.02521  -0.0561   0.9758   0.1611
  -1.250   0.0424   0.03448   0.02397  -0.0601   0.9651   0.1579
  -1.000   0.0913   0.03349   0.02279  -0.0642   0.9543   0.1611
  -0.750   0.1414   0.03283   0.02191  -0.0680   0.9428   0.1622
  -0.500   0.1852   0.03238   0.02131  -0.0706   0.9298   0.1658
  -0.250   0.2282   0.03208   0.02083  -0.0732   0.9162   0.1734
   0.000   0.2704   0.03162   0.02047  -0.0760   0.9026   0.1929
   0.250   0.3132   0.03107   0.02018  -0.0788   0.8889   0.2349
   0.500   0.3500   0.02902   0.01999  -0.0790   0.8761   1.0000
   0.750   0.3902   0.02946   0.01989  -0.0807   0.8612   1.0000
   1.000   0.4298   0.02985   0.01996  -0.0826   0.8462   1.0000
   1.250   0.4689   0.03019   0.02007  -0.0844   0.8310   1.0000
   1.500   0.5052   0.03050   0.02021  -0.0854   0.8157   1.0000
   1.750   0.5399   0.03077   0.02036  -0.0861   0.8001   1.0000
   2.000   0.5732   0.03102   0.02052  -0.0864   0.7844   1.0000
   2.250   0.6050   0.03127   0.02069  -0.0863   0.7687   1.0000
   2.500   0.6358   0.03148   0.02084  -0.0859   0.7528   1.0000
   2.750   0.6657   0.03168   0.02100  -0.0854   0.7371   1.0000
   3.000   0.6948   0.03189   0.02117  -0.0846   0.7216   1.0000
   3.250   0.7234   0.03207   0.02132  -0.0838   0.7062   1.0000
   3.500   0.7486   0.03249   0.02175  -0.0827   0.6902   1.0000
   3.750   0.7712   0.03315   0.02241  -0.0816   0.6738   1.0000
   4.000   0.7964   0.03365   0.02291  -0.0806   0.6589   1.0000
   4.250   0.8245   0.03395   0.02321  -0.0798   0.6457   1.0000
   4.500   0.8500   0.03449   0.02380  -0.0788   0.6322   1.0000
   4.750   0.8708   0.03552   0.02487  -0.0779   0.6179   1.0000
   5.000   0.8890   0.03689   0.02631  -0.0770   0.6040   1.0000
   5.250   0.9053   0.03851   0.02801  -0.0762   0.5909   1.0000
   5.500   0.9216   0.04016   0.02978  -0.0753   0.5785   1.0000
   5.750   0.9451   0.04114   0.03083  -0.0746   0.5683   1.0000
   6.000   0.9645   0.04259   0.03238  -0.0739   0.5580   1.0000
   6.250   0.9668   0.04577   0.03570  -0.0731   0.5459   1.0000
   6.500   0.9737   0.04855   0.03859  -0.0724   0.5355   1.0000
   6.750   1.0098   0.04818   0.03837  -0.0716   0.5272   1.0000
   7.000   1.0026   0.05218   0.04248  -0.0706   0.5146   1.0000
   7.250   1.0030   0.05522   0.04562  -0.0694   0.5020   1.0000
   7.500   1.0119   0.05726   0.04777  -0.0681   0.4896   1.0000
   7.750   1.0389   0.05727   0.04792  -0.0665   0.4781   1.0000
   8.000   1.0968   0.05398   0.04486  -0.0650   0.4683   1.0000
   8.250   1.0176   0.06627   0.05710  -0.0652   0.4567   1.0000
   8.500   0.9856   0.07373   0.06450  -0.0661   0.4469   1.0000
   8.750   1.0257   0.07254   0.06357  -0.0640   0.4369   1.0000
   9.000   0.9778   0.08211   0.07307  -0.0659   0.4282   1.0000
   9.250   0.9724   0.08672   0.07775  -0.0661   0.4198   1.0000
   9.500   1.0063   0.08657   0.07782  -0.0643   0.4086   1.0000
   9.750   0.9533   0.09689   0.08803  -0.0672   0.4033   1.0000
  10.000   0.9715   0.09884   0.09013  -0.0662   0.3926   1.0000
  10.250   0.9443   0.10658   0.09786  -0.0685   0.3908   1.0000
  10.500   0.9330   0.11301   0.10433  -0.0704   0.3918   1.0000
  10.750   0.9355   0.11857   0.11000  -0.0719   0.3941   1.0000
  11.000   1.3676   0.04594   0.03846  -0.0381   0.2407   1.0000
  11.250   1.3515   0.04695   0.03941  -0.0332   0.2149   1.0000
  11.500   1.3314   0.04897   0.04125  -0.0291   0.1901   1.0000
  11.750   1.3108   0.05217   0.04428  -0.0266   0.1674   1.0000
  12.000   1.2940   0.05603   0.04791  -0.0250   0.1473   1.0000
  12.250   1.2857   0.05970   0.05131  -0.0235   0.1297   1.0000
  12.500   1.2862   0.06304   0.05447  -0.0218   0.1154   1.0000
  12.750   1.2846   0.06688   0.05845  -0.0208   0.1066   1.0000
  13.000   1.2928   0.06988   0.06137  -0.0194   0.0980   1.0000
  13.250   1.2849   0.07444   0.06631  -0.0193   0.0947   1.0000
  13.500   1.2814   0.07876   0.07086  -0.0191   0.0916   1.0000
  13.750   1.0446   0.13476   0.12795  -0.0553   0.1737   1.0000
  14.000   0.9813   0.15911   0.15188  -0.0699   0.2106   1.0000
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