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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.96 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe10k-il-1000000-n5.txt
Download as CSV file: xf-goe10k-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 10K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5371   0.09005   0.08844  -0.0084   1.0000   0.0028
  -7.750  -0.5397   0.08692   0.08534  -0.0089   1.0000   0.0029
  -7.500  -0.5451   0.08444   0.08289  -0.0086   1.0000   0.0028
  -7.250  -0.5441   0.08042   0.07889  -0.0112   1.0000   0.0029
  -7.000  -0.5405   0.07679   0.07526  -0.0135   1.0000   0.0029
  -6.750  -0.5346   0.07249   0.07096  -0.0165   1.0000   0.0029
  -6.500  -0.5271   0.06834   0.06679  -0.0191   1.0000   0.0029
  -6.250  -0.5129   0.06348   0.06189  -0.0229   0.9997   0.0029
  -6.000  -0.4858   0.05736   0.05567  -0.0294   0.9982   0.0029
  -5.750  -0.4583   0.05176   0.04996  -0.0347   0.9966   0.0029
  -5.500  -0.4296   0.04628   0.04432  -0.0391   0.9953   0.0029
  -5.000  -0.3763   0.03470   0.03230  -0.0448   0.9908   0.0017
  -4.750  -0.3472   0.02927   0.02657  -0.0464   0.9889   0.0016
  -4.500  -0.3177   0.02412   0.02106  -0.0473   0.9875   0.0016
  -4.250  -0.2933   0.01833   0.01476  -0.0459   0.9844   0.0016
  -4.000  -0.2688   0.01267   0.00832  -0.0441   0.9818   0.0018
  -3.750  -0.2407   0.01110   0.00643  -0.0441   0.9803   0.0020
  -3.500  -0.2112   0.01033   0.00549  -0.0445   0.9792   0.0026
  -3.250  -0.1822   0.00915   0.00406  -0.0447   0.9782   0.0027
  -3.000  -0.1567   0.00836   0.00311  -0.0440   0.9756   0.0029
  -2.750  -0.1308   0.00774   0.00240  -0.0436   0.9726   0.0035
  -2.500  -0.1020   0.00739   0.00197  -0.0438   0.9706   0.0043
  -2.250  -0.0722   0.00709   0.00164  -0.0443   0.9690   0.0063
  -2.000  -0.0418   0.00680   0.00133  -0.0450   0.9677   0.0119
  -1.750  -0.0104   0.00648   0.00111  -0.0459   0.9664   0.0459
  -1.500   0.0126   0.00632   0.00098  -0.0448   0.9596   0.0625
  -1.250   0.0447   0.00602   0.00083  -0.0459   0.9550   0.1052
  -1.000   0.0764   0.00573   0.00069  -0.0469   0.9469   0.1690
  -0.750   0.1135   0.00536   0.00057  -0.0493   0.9388   0.2611
  -0.500   0.1461   0.00500   0.00048  -0.0506   0.9279   0.3722
  -0.250   0.1774   0.00456   0.00042  -0.0517   0.9144   0.5156
   0.000   0.2040   0.00411   0.00040  -0.0516   0.8961   0.6762
   0.250   0.2240   0.00371   0.00041  -0.0497   0.8680   0.8304
   0.750   0.3176   0.00524   0.00070  -0.0589   0.4517   0.9984
   1.000   0.3446   0.00569   0.00081  -0.0591   0.3518   1.0000
   1.250   0.3644   0.00620   0.00092  -0.0576   0.2349   1.0000
   1.500   0.3852   0.00667   0.00107  -0.0562   0.1389   1.0000
   1.750   0.4066   0.00711   0.00125  -0.0550   0.0661   1.0000
   2.000   0.4305   0.00729   0.00139  -0.0542   0.0507   1.0000
   2.250   0.4529   0.00767   0.00160  -0.0531   0.0108   1.0000
   2.500   0.4765   0.00793   0.00190  -0.0522   0.0062   1.0000
   2.750   0.4999   0.00823   0.00223  -0.0512   0.0043   1.0000
   3.000   0.5230   0.00858   0.00264  -0.0502   0.0036   1.0000
   3.250   0.5450   0.00913   0.00327  -0.0488   0.0031   1.0000
   3.500   0.5686   0.00942   0.00360  -0.0479   0.0023   1.0000
   3.750   0.5896   0.01017   0.00446  -0.0464   0.0019   1.0000
   4.000   0.6105   0.01112   0.00558  -0.0447   0.0018   1.0000
   4.250   0.6309   0.01273   0.00745  -0.0426   0.0017   1.0000
   4.500   0.6519   0.01517   0.01027  -0.0404   0.0017   1.0000
   4.750   0.6717   0.01832   0.01384  -0.0377   0.0017   1.0000
   5.000   0.6892   0.02171   0.01764  -0.0349   0.0019   1.0000
   5.500   0.7123   0.03094   0.02767  -0.0277   0.0033   1.0000
   5.750   0.7334   0.03514   0.03213  -0.0247   0.0024   1.0000
   6.000   0.7477   0.03761   0.03477  -0.0232   0.0021   1.0000
   7.500   0.7323   0.05449   0.05290  -0.0120   0.0020   1.0000
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