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GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 647 AIRFOIL (goe647-il)
Reynolds number: 50,000
Max Cl/Cd: 13.11 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe647-il-50000.txt
Download as CSV file: xf-goe647-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 647 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2620   0.11908   0.11335  -0.0140   1.0000   0.2688
  -8.250  -0.2921   0.12020   0.11461  -0.0115   1.0000   0.2743
  -8.000  -0.3389   0.12270   0.11730  -0.0089   1.0000   0.2760
  -7.750  -0.3072   0.11687   0.11148  -0.0072   1.0000   0.2806
  -7.500  -0.3106   0.11549   0.11017  -0.0050   1.0000   0.2854
  -7.250  -0.3334   0.11553   0.11032  -0.0028   1.0000   0.2917
  -7.000  -0.3931   0.11833   0.11330   0.0003   1.0000   0.2947
  -6.750  -0.3509   0.11220   0.10716  -0.0004   0.9982   0.2995
  -6.500  -0.3382   0.10979   0.10475  -0.0051   0.9878   0.3114
  -6.250  -0.3079   0.10528   0.10021  -0.0096   0.9778   0.3199
  -6.000  -0.3292   0.10507   0.10006  -0.0116   0.9656   0.3318
  -5.750  -0.2736   0.09928   0.09421  -0.0162   0.9553   0.3433
  -5.500  -0.2995   0.09840   0.09340  -0.0168   0.9420   0.3535
  -5.250  -0.2620   0.09428   0.08924  -0.0191   0.9305   0.3622
  -5.000  -0.3365   0.07095   0.06503  -0.0534   0.9234   0.1858
  -4.750  -0.3257   0.06161   0.05485  -0.0603   0.9140   0.1708
  -4.500  -0.2876   0.05737   0.05025  -0.0649   0.9034   0.1696
  -4.250  -0.2679   0.05387   0.04616  -0.0664   0.8907   0.1705
  -4.000  -0.2391   0.05229   0.04458  -0.0674   0.8774   0.1744
  -3.750  -0.2006   0.05001   0.04192  -0.0701   0.8653   0.1784
  -3.500  -0.1679   0.04785   0.03919  -0.0717   0.8524   0.1849
  -3.250  -0.1427   0.04692   0.03818  -0.0717   0.8383   0.1929
  -3.000  -0.1089   0.04559   0.03641  -0.0727   0.8254   0.2048
  -2.750  -0.0607   0.04449   0.03532  -0.0752   0.8135   0.2264
  -2.500  -0.0414   0.04412   0.03493  -0.0739   0.7984   0.2461
  -2.250  -0.0167   0.04372   0.03448  -0.0733   0.7841   0.2780
  -2.000   0.0147   0.04332   0.03432  -0.0730   0.7710   0.3262
  -1.750   0.0531   0.04273   0.03398  -0.0731   0.7594   0.3970
  -1.500   0.0669   0.04294   0.03428  -0.0704   0.7442   0.4430
  -1.250   0.0856   0.04298   0.03437  -0.0685   0.7300   0.4871
  -1.000   0.1223   0.04240   0.03381  -0.0684   0.7185   0.5362
  -0.750   0.1565   0.04192   0.03335  -0.0683   0.7061   0.5802
  -0.500   0.1718   0.04225   0.03377  -0.0663   0.6914   0.6186
  -0.250   0.1958   0.04213   0.03381  -0.0648   0.6790   0.6699
   0.000   0.2437   0.04060   0.03265  -0.0653   0.6700   0.7536
   0.250   0.3759   0.03923   0.03120  -0.0834   0.6548   1.0000
   0.500   0.3914   0.04024   0.03185  -0.0825   0.6416   1.0000
   0.750   0.4517   0.03924   0.03039  -0.0857   0.6337   1.0000
   1.000   0.4428   0.04142   0.03243  -0.0819   0.6192   1.0000
   1.250   0.5180   0.03950   0.03011  -0.0860   0.6139   1.0000
   1.500   0.4913   0.04273   0.03329  -0.0806   0.5989   1.0000
   1.750   0.4604   0.04656   0.03708  -0.0757   0.5856   1.0000
   2.000   0.5210   0.04516   0.03540  -0.0778   0.5796   1.0000
   2.250   0.4683   0.05088   0.04114  -0.0724   0.5660   1.0000
   2.500   0.5322   0.04896   0.03897  -0.0739   0.5610   1.0000
   2.750   0.4634   0.05656   0.04665  -0.0695   0.5495   1.0000
   3.000   0.5024   0.05655   0.04646  -0.0696   0.5434   1.0000
   3.250   0.4734   0.06151   0.05140  -0.0676   0.5361   1.0000
   3.500   0.4664   0.06489   0.05472  -0.0666   0.5301   1.0000
   3.750   0.4968   0.06584   0.05554  -0.0667   0.5252   1.0000
   4.000   0.3258   0.08334   0.07361  -0.0685   0.6222   1.0000
   4.250   0.4753   0.07389   0.06352  -0.0655   0.5204   1.0000
   4.500   0.4682   0.07768   0.06729  -0.0652   0.5199   1.0000
   4.750   0.4687   0.08118   0.07075  -0.0653   0.5208   1.0000
   5.000   0.4862   0.08421   0.07371  -0.0660   0.5231   1.0000
   5.500   0.3854   0.10005   0.08986  -0.0701   0.6309   1.0000
   5.750   0.3764   0.10058   0.09036  -0.0681   0.6208   1.0000
   6.000   0.4025   0.10365   0.09335  -0.0691   0.6156   1.0000
   6.250   0.4134   0.10643   0.09606  -0.0691   0.6120   1.0000
   6.500   0.4129   0.10744   0.09703  -0.0679   0.6017   1.0000
   6.750   0.4450   0.11119   0.10070  -0.0694   0.5964   1.0000
   7.000   0.4352   0.11207   0.10155  -0.0678   0.5883   1.0000
   7.250   0.4557   0.11467   0.10409  -0.0682   0.5807   1.0000
   7.500   0.4898   0.11931   0.10867  -0.0699   0.5775   1.0000
   7.750   0.4693   0.11896   0.10831  -0.0677   0.5684   1.0000
   8.000   0.4909   0.12185   0.11116  -0.0683   0.5623   1.0000
   8.250   0.5219   0.12658   0.11584  -0.0698   0.5590   1.0000
   8.500   0.5047   0.12600   0.11526  -0.0679   0.5482   1.0000
   8.750   0.5324   0.12966   0.11889  -0.0688   0.5429   1.0000
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