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GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 399 AIRFOIL (goe399-il)
Reynolds number: 500,000
Max Cl/Cd: 104.56 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe399-il-500000.txt
Download as CSV file: xf-goe399-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 399 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3568   0.08713   0.08498  -0.0277   1.0000   0.0196
  -7.500  -0.3641   0.08493   0.08284  -0.0279   1.0000   0.0197
  -7.250  -0.3654   0.08228   0.08023  -0.0283   1.0000   0.0197
  -7.000  -0.3673   0.07966   0.07764  -0.0286   1.0000   0.0198
  -6.750  -0.3595   0.07611   0.07409  -0.0313   0.9991   0.0198
  -6.500  -0.3351   0.06796   0.06591  -0.0410   0.9950   0.0203
  -6.250  -0.3122   0.06525   0.06318  -0.0431   0.9916   0.0211
  -6.000  -0.2807   0.06095   0.05884  -0.0497   0.9871   0.0219
  -5.750  -0.2441   0.05613   0.05395  -0.0578   0.9836   0.0231
  -5.500  -0.1944   0.05031   0.04793  -0.0686   0.9771   0.0266
  -4.750  -0.0972   0.03399   0.03106  -0.0842   0.9597   0.0291
  -4.500  -0.0661   0.03173   0.02868  -0.0863   0.9520   0.0316
  -4.250  -0.0393   0.01920   0.01487  -0.0871   0.9398   0.0272
  -4.000  -0.0138   0.01827   0.01387  -0.0874   0.9274   0.0296
  -3.750   0.0123   0.01772   0.01321  -0.0870   0.9135   0.0321
  -3.500   0.0368   0.01520   0.01021  -0.0861   0.8992   0.0335
  -3.250   0.0630   0.01426   0.00897  -0.0854   0.8848   0.0354
  -3.000   0.0877   0.01256   0.00689  -0.0846   0.8701   0.0375
  -2.750   0.1132   0.01163   0.00580  -0.0840   0.8551   0.0392
  -2.500   0.1393   0.01125   0.00530  -0.0835   0.8403   0.0412
  -2.250   0.1655   0.01088   0.00479  -0.0829   0.8265   0.0433
  -2.000   0.1916   0.01035   0.00413  -0.0824   0.8138   0.0444
  -1.750   0.2177   0.00993   0.00360  -0.0818   0.8015   0.0456
  -1.500   0.2440   0.00965   0.00322  -0.0813   0.7898   0.0469
  -1.250   0.2696   0.00920   0.00269  -0.0807   0.7787   0.0490
  -1.000   0.2952   0.00886   0.00229  -0.0801   0.7685   0.0518
  -0.750   0.3215   0.00871   0.00210  -0.0797   0.7582   0.0549
  -0.500   0.3480   0.00859   0.00194  -0.0792   0.7480   0.0587
  -0.250   0.3741   0.00840   0.00172  -0.0787   0.7382   0.0660
   0.000   0.4002   0.00828   0.00160  -0.0782   0.7277   0.0829
   0.250   0.4263   0.00815   0.00150  -0.0778   0.7160   0.1071
   0.500   0.4517   0.00793   0.00148  -0.0773   0.7035   0.1847
   0.750   0.5133   0.00601   0.00154  -0.0854   0.6887   1.0000
   1.000   0.5388   0.00610   0.00153  -0.0848   0.6755   1.0000
   1.250   0.5644   0.00618   0.00153  -0.0842   0.6631   1.0000
   1.500   0.5899   0.00627   0.00155  -0.0836   0.6499   1.0000
   1.750   0.6153   0.00637   0.00157  -0.0830   0.6359   1.0000
   2.000   0.6404   0.00648   0.00160  -0.0823   0.6180   1.0000
   2.250   0.6650   0.00662   0.00165  -0.0815   0.5959   1.0000
   2.500   0.6898   0.00676   0.00170  -0.0808   0.5740   1.0000
   2.750   0.7145   0.00693   0.00178  -0.0801   0.5528   1.0000
   3.000   0.7389   0.00712   0.00187  -0.0794   0.5292   1.0000
   3.250   0.7629   0.00735   0.00198  -0.0786   0.5027   1.0000
   3.500   0.7868   0.00760   0.00213  -0.0778   0.4791   1.0000
   3.750   0.8114   0.00782   0.00228  -0.0771   0.4622   1.0000
   4.000   0.8360   0.00804   0.00245  -0.0765   0.4466   1.0000
   4.250   0.8605   0.00826   0.00263  -0.0758   0.4315   1.0000
   4.500   0.8851   0.00848   0.00283  -0.0752   0.4165   1.0000
   4.750   0.9097   0.00870   0.00302  -0.0746   0.4014   1.0000
   5.000   0.9338   0.00895   0.00323  -0.0739   0.3827   1.0000
   5.250   0.9574   0.00924   0.00343  -0.0731   0.3509   1.0000
   5.500   0.9797   0.00966   0.00369  -0.0722   0.3062   1.0000
   5.750   0.9990   0.01038   0.00408  -0.0709   0.2433   1.0000
   6.000   1.0111   0.01188   0.00488  -0.0686   0.1148   1.0000
   6.250   1.0293   0.01280   0.00555  -0.0671   0.0716   1.0000
   6.500   1.0509   0.01332   0.00605  -0.0661   0.0609   1.0000
   6.750   1.0731   0.01377   0.00655  -0.0652   0.0527   1.0000
   7.000   1.0945   0.01430   0.00708  -0.0642   0.0419   1.0000
   7.250   1.1150   0.01492   0.00765  -0.0630   0.0287   1.0000
   7.500   1.1339   0.01568   0.00841  -0.0615   0.0231   1.0000
   7.750   1.1540   0.01628   0.00906  -0.0602   0.0203   1.0000
   8.000   1.1679   0.01744   0.01030  -0.0580   0.0176   1.0000
   8.250   1.1862   0.01813   0.01109  -0.0564   0.0167   1.0000
   8.500   1.2024   0.01898   0.01203  -0.0546   0.0158   1.0000
   8.750   1.2171   0.01991   0.01304  -0.0526   0.0149   1.0000
   9.000   1.2307   0.02089   0.01410  -0.0504   0.0142   1.0000
   9.250   1.2421   0.02202   0.01531  -0.0480   0.0137   1.0000
   9.500   1.2461   0.02378   0.01718  -0.0446   0.0128   1.0000
   9.750   1.2507   0.02579   0.01934  -0.0412   0.0123   1.0000
  10.000   1.2634   0.02657   0.02022  -0.0391   0.0119   1.0000
  10.250   1.2739   0.02784   0.02163  -0.0368   0.0115   1.0000
  10.500   1.2837   0.02948   0.02341  -0.0346   0.0112   1.0000
  10.750   1.2933   0.03108   0.02517  -0.0324   0.0109   1.0000
  11.000   1.3018   0.03303   0.02729  -0.0303   0.0107   1.0000
  11.250   1.3084   0.03498   0.02941  -0.0281   0.0104   1.0000
  11.500   1.3128   0.03706   0.03169  -0.0260   0.0101   1.0000
  11.750   1.3148   0.03955   0.03439  -0.0238   0.0100   1.0000
  12.000   1.3152   0.04175   0.03674  -0.0219   0.0097   1.0000
  12.250   1.3085   0.04536   0.04065  -0.0197   0.0098   1.0000
  12.500   1.2986   0.04912   0.04469  -0.0180   0.0099   1.0000
  12.750   1.2827   0.05371   0.04957  -0.0168   0.0099   1.0000
  13.000   1.2545   0.06046   0.05670  -0.0164   0.0103   1.0000
  13.250   1.2318   0.06645   0.06295  -0.0171   0.0105   1.0000
  13.500   1.2066   0.07325   0.06998  -0.0190   0.0108   1.0000
  13.750   1.1845   0.07992   0.07685  -0.0217   0.0109   1.0000
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