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GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 399 AIRFOIL (goe399-il)
Reynolds number: 200,000
Max Cl/Cd: 79.26 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe399-il-200000.txt
Download as CSV file: xf-goe399-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3512   0.09678   0.09328  -0.0282   1.0000   0.0355
  -8.000  -0.3563   0.09516   0.09173  -0.0294   1.0000   0.0357
  -7.750  -0.3604   0.09321   0.08985  -0.0304   1.0000   0.0359
  -7.500  -0.3591   0.09067   0.08736  -0.0332   1.0000   0.0361
  -7.250  -0.3558   0.08786   0.08459  -0.0352   1.0000   0.0361
  -7.000  -0.3520   0.08493   0.08168  -0.0367   1.0000   0.0362
  -6.750  -0.3568   0.07970   0.07652  -0.0351   1.0000   0.0368
  -6.500  -0.3576   0.07662   0.07349  -0.0313   1.0000   0.0375
  -6.250  -0.3574   0.07423   0.07114  -0.0293   1.0000   0.0380
  -6.000  -0.3581   0.07203   0.06898  -0.0277   1.0000   0.0388
  -5.750  -0.3598   0.06997   0.06695  -0.0266   1.0000   0.0396
  -5.500  -0.3481   0.06697   0.06394  -0.0287   0.9983   0.0413
  -5.250  -0.3038   0.06166   0.05850  -0.0393   0.9926   0.0453
  -5.000  -0.2525   0.05426   0.05079  -0.0526   0.9858   0.0489
  -4.750  -0.2240   0.05089   0.04743  -0.0553   0.9808   0.0513
  -4.500  -0.1848   0.04697   0.04335  -0.0610   0.9740   0.0560
  -4.250  -0.1319   0.04088   0.03675  -0.0701   0.9693   0.0619
  -4.000  -0.1040   0.03840   0.03432  -0.0719   0.9610   0.0660
  -3.750  -0.0564   0.03415   0.02953  -0.0776   0.9566   0.0760
  -3.500  -0.0248   0.03159   0.02694  -0.0796   0.9486   0.0801
  -3.250   0.0161   0.02856   0.02353  -0.0830   0.9438   0.0915
  -3.000   0.0502   0.02653   0.02125  -0.0849   0.9370   0.1052
  -2.750   0.0898   0.02196   0.01579  -0.0852   0.9304   0.0724
  -2.500   0.1233   0.01974   0.01320  -0.0861   0.9235   0.0718
  -2.250   0.1554   0.01771   0.01084  -0.0865   0.9155   0.0697
  -2.000   0.1863   0.01635   0.00919  -0.0866   0.9065   0.0696
  -1.750   0.2192   0.01559   0.00819  -0.0870   0.8990   0.0729
  -1.500   0.2473   0.01486   0.00726  -0.0865   0.8881   0.0740
  -1.250   0.2753   0.01365   0.00600  -0.0863   0.8781   0.0765
  -1.000   0.3039   0.01299   0.00533  -0.0860   0.8686   0.0803
  -0.750   0.3308   0.01255   0.00484  -0.0854   0.8575   0.0859
  -0.500   0.3565   0.01204   0.00436  -0.0848   0.8460   0.0952
  -0.250   0.3822   0.01157   0.00392  -0.0840   0.8347   0.1085
   0.000   0.4078   0.01114   0.00358  -0.0833   0.8235   0.1395
   0.250   0.4679   0.00873   0.00330  -0.0903   0.8144   1.0000
   0.500   0.4931   0.00882   0.00322  -0.0894   0.8015   1.0000
   0.750   0.5183   0.00891   0.00317  -0.0886   0.7885   1.0000
   1.000   0.5434   0.00902   0.00316  -0.0877   0.7752   1.0000
   1.250   0.5684   0.00912   0.00315  -0.0868   0.7608   1.0000
   1.500   0.5931   0.00923   0.00314  -0.0858   0.7448   1.0000
   1.750   0.6178   0.00935   0.00314  -0.0849   0.7284   1.0000
   2.000   0.6426   0.00948   0.00316  -0.0840   0.7126   1.0000
   2.250   0.6674   0.00961   0.00325  -0.0831   0.6970   1.0000
   2.500   0.6921   0.00975   0.00334  -0.0823   0.6805   1.0000
   2.750   0.7167   0.00989   0.00343  -0.0814   0.6631   1.0000
   3.000   0.7412   0.01004   0.00352  -0.0806   0.6448   1.0000
   3.250   0.7655   0.01020   0.00359  -0.0796   0.6253   1.0000
   3.500   0.7895   0.01035   0.00372  -0.0787   0.6034   1.0000
   3.750   0.8137   0.01054   0.00383  -0.0778   0.5838   1.0000
   4.000   0.8378   0.01074   0.00400  -0.0769   0.5633   1.0000
   4.250   0.8619   0.01097   0.00418  -0.0761   0.5439   1.0000
   4.500   0.8857   0.01122   0.00440  -0.0752   0.5251   1.0000
   4.750   0.9095   0.01148   0.00464  -0.0743   0.5052   1.0000
   5.000   0.9329   0.01177   0.00489  -0.0734   0.4860   1.0000
   5.250   0.9560   0.01208   0.00517  -0.0724   0.4649   1.0000
   5.500   0.9790   0.01241   0.00551  -0.0715   0.4448   1.0000
   5.750   1.0018   0.01276   0.00585  -0.0705   0.4258   1.0000
   6.000   1.0232   0.01311   0.00618  -0.0693   0.3971   1.0000
   6.250   1.0431   0.01347   0.00649  -0.0678   0.3519   1.0000
   6.500   1.0582   0.01428   0.00691  -0.0657   0.2633   1.0000
   6.750   1.0613   0.01658   0.00819  -0.0624   0.1097   1.0000
   7.000   1.0750   0.01794   0.00939  -0.0603   0.0806   1.0000
   7.250   1.0889   0.01921   0.01066  -0.0581   0.0621   1.0000
   7.500   1.0986   0.02082   0.01230  -0.0553   0.0502   1.0000
   7.750   1.1061   0.02270   0.01415  -0.0523   0.0435   1.0000
   8.000   1.1237   0.02355   0.01512  -0.0506   0.0383   1.0000
   8.250   1.1367   0.02497   0.01656  -0.0485   0.0349   1.0000
   8.500   1.1510   0.02728   0.01889  -0.0466   0.0328   1.0000
   8.750   1.1707   0.02876   0.02052  -0.0452   0.0311   1.0000
   9.000   1.1896   0.03016   0.02205  -0.0439   0.0289   1.0000
   9.250   1.2066   0.03148   0.02347  -0.0425   0.0269   1.0000
   9.500   1.2259   0.03365   0.02571  -0.0416   0.0256   1.0000
   9.750   1.2484   0.03754   0.02985  -0.0413   0.0248   1.0000
  10.000   1.2653   0.04151   0.03415  -0.0401   0.0247   1.0000
  10.250   1.2769   0.04494   0.03791  -0.0383   0.0247   1.0000
  10.500   1.2849   0.04796   0.04124  -0.0361   0.0249   1.0000
  10.750   1.2851   0.05228   0.04592  -0.0336   0.0247   1.0000
  11.000   1.2822   0.05606   0.05001  -0.0308   0.0247   1.0000
  11.250   1.2722   0.06017   0.05442  -0.0277   0.0246   1.0000
  11.500   1.2595   0.06335   0.05784  -0.0242   0.0246   1.0000
  11.750   1.2522   0.06501   0.05968  -0.0213   0.0248   1.0000
  12.000   1.2386   0.06718   0.06209  -0.0187   0.0252   1.0000
  12.250   1.0787   0.07063   0.06646  -0.0134   0.0286   1.0000
  12.500   1.0488   0.07757   0.07362  -0.0149   0.0295   1.0000
  12.750   1.0203   0.08457   0.08079  -0.0174   0.0301   1.0000
  13.000   0.9915   0.09195   0.08832  -0.0207   0.0307   1.0000
  13.250   0.9625   0.09951   0.09602  -0.0248   0.0313   1.0000
  13.500   0.9316   0.10723   0.10385  -0.0297   0.0316   1.0000
  13.750   0.8971   0.11530   0.11205  -0.0356   0.0317   1.0000
  14.000   0.8723   0.12311   0.11991  -0.0405   0.0325   1.0000
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