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GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 681 AIRFOIL (goe681-il)
Reynolds number: 50,000
Max Cl/Cd: 26.52 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe681-il-50000-n5.txt
Download as CSV file: xf-goe681-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 681 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3020   0.11188   0.10462  -0.0437   1.0000   0.0823
 -10.000  -0.3162   0.10956   0.10240  -0.0422   1.0000   0.0819
  -9.750  -0.3322   0.10719   0.10013  -0.0407   1.0000   0.0814
  -9.500  -0.3319   0.10219   0.09515  -0.0446   0.9947   0.0815
  -9.250  -0.3310   0.09602   0.08898  -0.0503   0.9865   0.0820
  -9.000  -0.3352   0.08920   0.08215  -0.0566   0.9780   0.0822
  -8.750  -0.3584   0.07898   0.07190  -0.0658   0.9675   0.0822
  -8.500  -0.4204   0.06664   0.05930  -0.0748   0.9496   0.0810
  -8.250  -0.4473   0.05932   0.05156  -0.0780   0.9359   0.0810
  -8.000  -0.4562   0.05442   0.04623  -0.0788   0.9246   0.0818
  -7.750  -0.4586   0.05077   0.04216  -0.0782   0.9140   0.0827
  -7.500  -0.4480   0.04718   0.03802  -0.0788   0.9063   0.0839
  -7.250  -0.4389   0.04489   0.03538  -0.0776   0.8970   0.0851
  -7.000  -0.4158   0.04344   0.03386  -0.0778   0.8900   0.0868
  -6.750  -0.3885   0.04182   0.03205  -0.0788   0.8846   0.0894
  -6.500  -0.3781   0.04050   0.03046  -0.0768   0.8745   0.0922
  -6.250  -0.3498   0.03915   0.02899  -0.0776   0.8690   0.0960
  -6.000  -0.3305   0.03823   0.02798  -0.0767   0.8613   0.0998
  -5.750  -0.3098   0.03708   0.02661  -0.0759   0.8534   0.1044
  -5.500  -0.2779   0.03607   0.02560  -0.0769   0.8486   0.1105
  -5.250  -0.2625   0.03545   0.02494  -0.0751   0.8399   0.1169
  -5.000  -0.2388   0.03479   0.02424  -0.0747   0.8328   0.1270
  -4.750  -0.2050   0.03418   0.02368  -0.0758   0.8281   0.1413
  -4.500  -0.1927   0.03409   0.02358  -0.0734   0.8186   0.1536
  -4.250  -0.1670   0.03390   0.02336  -0.0731   0.8117   0.1707
  -4.000  -0.1322   0.03373   0.02301  -0.0742   0.8072   0.1972
  -3.750  -0.1257   0.03405   0.02340  -0.0709   0.7965   0.2120
  -3.500  -0.0981   0.03390   0.02317  -0.0709   0.7902   0.2345
  -3.250  -0.0604   0.03336   0.02258  -0.0722   0.7862   0.2543
  -3.000  -0.0546   0.03349   0.02271  -0.0688   0.7748   0.2641
  -2.750  -0.0210   0.03308   0.02216  -0.0695   0.7691   0.2814
  -2.500   0.0149   0.03264   0.02165  -0.0705   0.7641   0.2984
  -2.250   0.0256   0.03276   0.02181  -0.0678   0.7526   0.3092
  -2.000   0.0664   0.03218   0.02118  -0.0694   0.7472   0.3288
  -1.750   0.0824   0.03222   0.02115  -0.0674   0.7356   0.3434
  -1.500   0.1208   0.03159   0.02050  -0.0685   0.7284   0.3626
  -1.250   0.1421   0.03141   0.02037  -0.0671   0.7177   0.3769
  -1.000   0.1762   0.03086   0.01983  -0.0674   0.7095   0.3958
  -0.750   0.2015   0.03058   0.01959  -0.0666   0.7000   0.4146
  -0.500   0.2287   0.03020   0.01929  -0.0660   0.6908   0.4390
  -0.250   0.2601   0.02963   0.01886  -0.0659   0.6833   0.4741
   0.000   0.2771   0.02944   0.01889  -0.0638   0.6722   0.5170
   0.250   0.3161   0.02825   0.01826  -0.0640   0.6668   0.6263
   0.500   0.3987   0.02787   0.01854  -0.0723   0.6539   0.8958
   0.750   0.5002   0.02734   0.01771  -0.0848   0.6445   1.0000
   1.000   0.5124   0.02749   0.01768  -0.0820   0.6326   1.0000
   1.250   0.5264   0.02763   0.01765  -0.0795   0.6210   1.0000
   1.500   0.5527   0.02741   0.01723  -0.0786   0.6110   1.0000
   1.750   0.5607   0.02776   0.01746  -0.0752   0.5977   1.0000
   2.000   0.5854   0.02762   0.01713  -0.0741   0.5871   1.0000
   2.250   0.6007   0.02778   0.01716  -0.0717   0.5746   1.0000
   2.500   0.6132   0.02805   0.01731  -0.0689   0.5615   1.0000
   2.750   0.6404   0.02788   0.01695  -0.0682   0.5507   1.0000
   3.000   0.6521   0.02821   0.01718  -0.0653   0.5371   1.0000
   3.250   0.6658   0.02853   0.01740  -0.0628   0.5241   1.0000
   3.500   0.6916   0.02849   0.01717  -0.0619   0.5130   1.0000
   3.750   0.7041   0.02891   0.01749  -0.0593   0.5000   1.0000
   4.000   0.7186   0.02931   0.01779  -0.0571   0.4877   1.0000
   4.250   0.7466   0.02930   0.01758  -0.0565   0.4777   1.0000
   4.500   0.7534   0.03001   0.01824  -0.0534   0.4655   1.0000
   4.750   0.7736   0.03032   0.01841  -0.0520   0.4556   1.0000
   5.000   0.7892   0.03081   0.01882  -0.0500   0.4454   1.0000
   5.250   0.8061   0.03133   0.01923  -0.0483   0.4362   1.0000
   5.500   0.8236   0.03185   0.01966  -0.0467   0.4273   1.0000
   5.750   0.8429   0.03239   0.02011  -0.0454   0.4195   1.0000
   6.000   0.8560   0.03314   0.02083  -0.0435   0.4113   1.0000
   6.250   0.8852   0.03338   0.02089  -0.0434   0.4047   1.0000
   6.500   0.8888   0.03456   0.02214  -0.0405   0.3969   1.0000
   6.750   0.9111   0.03509   0.02258  -0.0397   0.3906   1.0000
   7.000   0.9322   0.03575   0.02317  -0.0389   0.3850   1.0000
   7.250   0.9375   0.03704   0.02454  -0.0364   0.3787   1.0000
   7.500   0.9582   0.03773   0.02519  -0.0356   0.3734   1.0000
   7.750   0.9903   0.03804   0.02537  -0.0360   0.3689   1.0000
   8.000   0.9824   0.03999   0.02748  -0.0325   0.3632   1.0000
   8.250   0.9920   0.04126   0.02879  -0.0308   0.3581   1.0000
   8.500   1.0172   0.04183   0.02931  -0.0305   0.3540   1.0000
   8.750   1.0398   0.04264   0.03008  -0.0300   0.3503   1.0000
   9.000   1.0169   0.04579   0.03345  -0.0262   0.3454   1.0000
   9.250   1.0112   0.04825   0.03603  -0.0240   0.3408   1.0000
   9.500   1.0279   0.04936   0.03714  -0.0232   0.3372   1.0000
   9.750   1.0629   0.04935   0.03708  -0.0235   0.3343   1.0000
  10.000   0.9337   0.06260   0.05077  -0.0188   0.3249   1.0000
  10.250   0.9164   0.06754   0.05579  -0.0185   0.3196   1.0000
  10.500   0.9357   0.06848   0.05674  -0.0179   0.3173   1.0000
  10.750   0.9651   0.06833   0.05658  -0.0172   0.3157   1.0000
  11.250   0.8380   0.09233   0.08087  -0.0217   0.2980   1.0000
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