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GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 492 AIRFOIL (goe492-il)
Reynolds number: 100,000
Max Cl/Cd: 57.2 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe492-il-100000.txt
Download as CSV file: xf-goe492-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 492 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4136   0.09375   0.08902  -0.0312   1.0000   0.0752
  -7.500  -0.4256   0.09237   0.08778  -0.0339   1.0000   0.0760
  -7.250  -0.4307   0.09014   0.08561  -0.0398   1.0000   0.0765
  -7.000  -0.4223   0.08501   0.08053  -0.0309   1.0000   0.0791
  -6.750  -0.4197   0.08236   0.07792  -0.0291   1.0000   0.0822
  -6.500  -0.4204   0.07974   0.07535  -0.0298   1.0000   0.0852
  -6.250  -0.4179   0.07675   0.07228  -0.0421   1.0000   0.0898
  -6.000  -0.4172   0.07259   0.06822  -0.0379   1.0000   0.0915
  -5.750  -0.4135   0.07012   0.06580  -0.0338   1.0000   0.0948
  -5.500  -0.3957   0.06577   0.06120  -0.0453   1.0000   0.1041
  -5.250  -0.3947   0.06280   0.05836  -0.0392   1.0000   0.1067
  -5.000  -0.3758   0.05888   0.05422  -0.0451   1.0000   0.1184
  -4.750  -0.3712   0.05684   0.05232  -0.0403   1.0000   0.1266
  -4.500  -0.3524   0.05326   0.04856  -0.0443   1.0000   0.1463
  -4.250  -0.3398   0.05067   0.04597  -0.0432   1.0000   0.1611
  -4.000  -0.3243   0.04805   0.04332  -0.0429   1.0000   0.1768
  -3.500  -0.2184   0.02889   0.02160  -0.0592   1.0000   0.0748
  -3.250  -0.1893   0.02619   0.01823  -0.0595   1.0000   0.0756
  -3.000  -0.1622   0.02363   0.01529  -0.0597   1.0000   0.0800
  -2.750  -0.1354   0.02183   0.01312  -0.0594   1.0000   0.0833
  -2.500  -0.1099   0.02053   0.01144  -0.0589   1.0000   0.0928
  -2.250  -0.0855   0.01957   0.01030  -0.0583   1.0000   0.1022
  -2.000  -0.0619   0.01862   0.00936  -0.0577   1.0000   0.1133
  -1.750  -0.0388   0.01792   0.00867  -0.0571   1.0000   0.1252
  -1.500  -0.0159   0.01736   0.00816  -0.0565   1.0000   0.1390
  -1.250   0.0069   0.01691   0.00791  -0.0559   1.0000   0.1699
  -1.000   0.0303   0.01630   0.00804  -0.0557   1.0000   0.3678
  -0.750   0.0542   0.01580   0.00823  -0.0556   1.0000   0.5358
  -0.500   0.0990   0.01512   0.00832  -0.0590   0.9924   1.0000
  -0.250   0.1443   0.01568   0.00858  -0.0631   0.9838   1.0000
   0.000   0.1862   0.01612   0.00877  -0.0665   0.9739   1.0000
   0.250   0.2285   0.01655   0.00903  -0.0699   0.9646   1.0000
   0.500   0.2739   0.01696   0.00931  -0.0739   0.9563   1.0000
   0.750   0.3115   0.01724   0.00951  -0.0763   0.9454   1.0000
   1.000   0.3496   0.01753   0.00974  -0.0787   0.9350   1.0000
   1.250   0.3913   0.01778   0.00997  -0.0817   0.9263   1.0000
   1.500   0.4318   0.01797   0.01017  -0.0844   0.9169   1.0000
   1.750   0.4664   0.01818   0.01044  -0.0859   0.9060   1.0000
   2.000   0.5037   0.01835   0.01067  -0.0879   0.8962   1.0000
   2.250   0.5493   0.01835   0.01078  -0.0913   0.8891   1.0000
   2.500   0.5831   0.01847   0.01101  -0.0925   0.8778   1.0000
   2.750   0.6210   0.01845   0.01119  -0.0941   0.8670   1.0000
   3.000   0.6614   0.01822   0.01115  -0.0958   0.8560   1.0000
   3.250   0.7045   0.01782   0.01099  -0.0977   0.8461   1.0000
   3.500   0.7413   0.01694   0.01035  -0.0973   0.8253   1.0000
   3.750   0.7801   0.01392   0.00743  -0.0923   0.7537   1.0000
   4.000   0.7899   0.01381   0.00626  -0.0843   0.5218   1.0000
   4.250   0.7791   0.01804   0.00779  -0.0779   0.0949   1.0000
   4.500   0.7965   0.01942   0.00911  -0.0757   0.0721   1.0000
   4.750   0.8123   0.02084   0.01052  -0.0734   0.0618   1.0000
   5.000   0.8307   0.02227   0.01203  -0.0713   0.0579   1.0000
   5.250   0.8534   0.02405   0.01379  -0.0699   0.0553   1.0000
   5.500   0.8819   0.02625   0.01597  -0.0693   0.0532   1.0000
   5.750   0.9120   0.02947   0.01926  -0.0693   0.0493   1.0000
   6.000   0.9415   0.03251   0.02254  -0.0688   0.0495   1.0000
   6.250   0.9700   0.03438   0.02479  -0.0674   0.0521   1.0000
   6.500   0.9968   0.03838   0.02946  -0.0654   0.0602   1.0000
   6.750   1.0319   0.04431   0.03605  -0.0633   0.0887   1.0000
   9.000   1.1122   0.08755   0.08240  -0.0471   0.1143   1.0000
   9.250   1.0810   0.08903   0.08431  -0.0441   0.1137   1.0000
   9.500   1.0505   0.09184   0.08728  -0.0422   0.1132   1.0000
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