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GOE 627 AIRFOIL (goe627-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 627 AIRFOIL (goe627-il)
Reynolds number: 100,000
Max Cl/Cd: 43.33 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe627-il-100000.txt
Download as CSV file: xf-goe627-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 627 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3595   0.10935   0.10472  -0.0301   1.0000   0.1452
  -9.500  -0.3551   0.10723   0.10263  -0.0282   1.0000   0.1492
  -9.250  -0.3726   0.10495   0.10043  -0.0279   1.0000   0.1544
  -9.000  -0.4405   0.10267   0.09834  -0.0307   1.0000   0.1571
  -8.750  -0.4091   0.09898   0.09466  -0.0266   1.0000   0.1604
  -8.500  -0.3984   0.09711   0.09281  -0.0236   1.0000   0.1643
  -8.250  -0.4142   0.09493   0.09071  -0.0222   1.0000   0.1689
  -8.000  -0.4661   0.09254   0.08846  -0.0218   1.0000   0.1721
  -7.750  -0.5409   0.09050   0.08646  -0.0198   1.0000   0.1735
  -7.500  -0.5502   0.08663   0.08265  -0.0175   1.0000   0.1760
  -7.250  -0.5252   0.08510   0.08121  -0.0139   1.0000   0.1794
  -7.000  -0.5363   0.08305   0.07919  -0.0113   1.0000   0.1841
  -6.750  -0.5776   0.07849   0.07450  -0.0129   0.9975   0.1931
  -6.500  -0.5373   0.07607   0.07215  -0.0139   0.9918   0.2001
  -6.250  -0.5195   0.07195   0.06794  -0.0180   0.9827   0.2144
  -6.000  -0.5610   0.04703   0.04032  -0.0234   0.9703   0.1008
  -5.750  -0.5353   0.04398   0.03691  -0.0236   0.9608   0.0963
  -5.500  -0.5035   0.04073   0.03316  -0.0248   0.9537   0.0926
  -5.250  -0.4776   0.03841   0.03037  -0.0245   0.9437   0.0916
  -5.000  -0.4453   0.03678   0.02841  -0.0254   0.9349   0.0927
  -4.750  -0.4094   0.03511   0.02639  -0.0266   0.9264   0.0931
  -4.500  -0.3775   0.03378   0.02479  -0.0271   0.9168   0.0936
  -4.250  -0.3349   0.03256   0.02334  -0.0293   0.9094   0.0955
  -4.000  -0.3045   0.03172   0.02231  -0.0294   0.8988   0.0984
  -3.750  -0.2573   0.03034   0.02095  -0.0326   0.8925   0.1016
  -3.500  -0.2289   0.02951   0.02018  -0.0324   0.8812   0.1049
  -3.250  -0.1798   0.02852   0.01918  -0.0356   0.8754   0.1113
  -3.000  -0.1563   0.02775   0.01854  -0.0346   0.8630   0.1181
  -2.750  -0.1195   0.02683   0.01772  -0.0356   0.8548   0.1310
  -2.500  -0.0891   0.02579   0.01688  -0.0354   0.8449   0.1597
  -2.250  -0.0796   0.02347   0.01637  -0.0318   0.8342   0.4610
  -2.000   0.0001   0.02245   0.01682  -0.0378   0.8306   0.8501
  -1.750   0.2335   0.02324   0.01718  -0.0696   0.8427   0.9554
  -1.500   0.3464   0.02235   0.01603  -0.0843   0.8371   0.9748
  -1.250   0.4443   0.02101   0.01449  -0.0969   0.8291   0.9899
  -1.000   0.5205   0.01974   0.01305  -0.1059   0.8164   1.0000
  -0.750   0.5543   0.01901   0.01219  -0.1069   0.7991   1.0000
  -0.500   0.5871   0.01839   0.01142  -0.1077   0.7796   1.0000
  -0.250   0.6199   0.01787   0.01072  -0.1085   0.7584   1.0000
   0.000   0.6443   0.01760   0.01028  -0.1077   0.7341   1.0000
   0.250   0.6680   0.01743   0.00990  -0.1068   0.7088   1.0000
   0.500   0.6902   0.01736   0.00962  -0.1056   0.6831   1.0000
   0.750   0.7084   0.01740   0.00946  -0.1037   0.6567   1.0000
   1.000   0.7275   0.01750   0.00932  -0.1020   0.6318   1.0000
   1.250   0.7422   0.01768   0.00933  -0.0995   0.6065   1.0000
   1.500   0.7588   0.01788   0.00931  -0.0974   0.5835   1.0000
   1.750   0.7753   0.01813   0.00934  -0.0952   0.5622   1.0000
   2.000   0.7894   0.01840   0.00947  -0.0927   0.5416   1.0000
   2.250   0.8042   0.01869   0.00960  -0.0903   0.5226   1.0000
   2.500   0.8196   0.01900   0.00975  -0.0881   0.5054   1.0000
   2.750   0.8360   0.01933   0.00992  -0.0860   0.4898   1.0000
   3.250   0.8684   0.02005   0.01039  -0.0818   0.4620   1.0000
   3.500   0.8851   0.02047   0.01073  -0.0798   0.4502   1.0000
   3.750   0.9064   0.02092   0.01099  -0.0787   0.4398   1.0000
   4.000   0.9208   0.02135   0.01142  -0.0763   0.4293   1.0000
   4.250   0.9408   0.02184   0.01180  -0.0750   0.4204   1.0000
   4.500   0.9569   0.02229   0.01224  -0.0729   0.4115   1.0000
   4.750   0.9790   0.02283   0.01265  -0.0721   0.4040   1.0000
   5.000   0.9933   0.02335   0.01323  -0.0697   0.3966   1.0000
   5.250   1.0169   0.02389   0.01366  -0.0691   0.3903   1.0000
   5.500   1.0330   0.02452   0.01433  -0.0671   0.3842   1.0000
   5.750   1.0486   0.02507   0.01492  -0.0650   0.3779   1.0000
   6.000   1.0742   0.02566   0.01538  -0.0648   0.3724   1.0000
   6.250   1.0880   0.02635   0.01617  -0.0625   0.3672   1.0000
   6.500   1.1023   0.02702   0.01693  -0.0602   0.3623   1.0000
   6.750   1.1233   0.02766   0.01757  -0.0592   0.3577   1.0000
   7.000   1.1501   0.02846   0.01826  -0.0593   0.3534   1.0000
   7.250   1.1565   0.02923   0.01925  -0.0557   0.3489   1.0000
   7.500   1.1698   0.02998   0.02009  -0.0534   0.3444   1.0000
   7.750   1.1903   0.03068   0.02080  -0.0523   0.3402   1.0000
   8.000   1.2188   0.03162   0.02165  -0.0529   0.3365   1.0000
   8.250   1.2196   0.03259   0.02288  -0.0485   0.3328   1.0000
   8.500   1.2280   0.03351   0.02395  -0.0455   0.3286   1.0000
   8.750   1.2446   0.03430   0.02479  -0.0439   0.3246   1.0000
   9.000   1.2772   0.03502   0.02537  -0.0450   0.3201   1.0000
   9.250   1.2704   0.03614   0.02676  -0.0396   0.3161   1.0000
   9.500   1.2740   0.03702   0.02777  -0.0359   0.3111   1.0000
   9.750   1.2969   0.03744   0.02816  -0.0353   0.3060   1.0000
  10.000   1.3168   0.03834   0.02905  -0.0345   0.3016   1.0000
  10.250   1.3035   0.03973   0.03071  -0.0284   0.2980   1.0000
  10.500   1.3041   0.04087   0.03199  -0.0247   0.2940   1.0000
  10.750   1.3247   0.04152   0.03265  -0.0239   0.2898   1.0000
  11.000   1.3555   0.04237   0.03344  -0.0248   0.2856   1.0000
  11.250   1.3220   0.04425   0.03562  -0.0162   0.2829   1.0000
  11.500   1.2937   0.04623   0.03781  -0.0091   0.2798   1.0000
  11.750   1.2934   0.04748   0.03916  -0.0059   0.2757   1.0000
  12.000   1.3742   0.04673   0.03817  -0.0130   0.2697   1.0000
  12.250   1.3175   0.04966   0.04142  -0.0029   0.2678   1.0000
  12.500   1.2422   0.05484   0.04691   0.0060   0.2658   1.0000
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