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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 50,000
Max Cl/Cd: 20.6 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe10k-il-50000.txt
Download as CSV file: xf-goe10k-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5491   0.10529   0.09845  -0.0053   1.0000   0.1573
  -8.000  -0.5542   0.10329   0.09655  -0.0065   1.0000   0.1639
  -7.750  -0.5702   0.10272   0.09614  -0.0108   1.0000   0.1659
  -7.500  -0.5532   0.09679   0.09018  -0.0068   1.0000   0.1778
  -7.250  -0.5501   0.09296   0.08642  -0.0069   1.0000   0.1854
  -7.000  -0.5566   0.09132   0.08487  -0.0113   1.0000   0.1949
  -6.750  -0.5478   0.08685   0.08044  -0.0090   1.0000   0.2085
  -6.500  -0.5435   0.08329   0.07693  -0.0088   1.0000   0.2230
  -6.250  -0.5435   0.08062   0.07430  -0.0111   1.0000   0.2399
  -6.000  -0.5338   0.07621   0.06997  -0.0062   1.0000   0.2642
  -5.750  -0.5298   0.07290   0.06673  -0.0046   1.0000   0.2908
  -5.500  -0.5248   0.06978   0.06367  -0.0016   1.0000   0.3242
  -5.250  -0.5214   0.06668   0.06065   0.0027   1.0000   0.3667
  -4.500  -0.3662   0.05049   0.04405   0.0275   1.0000   0.7976
  -4.250  -0.3902   0.04951   0.04326   0.0316   1.0000   0.7756
  -4.000  -0.4191   0.04844   0.04240   0.0351   1.0000   0.7357
  -3.750  -0.3525   0.03868   0.03018  -0.0322   1.0000   0.1487
  -3.500  -0.3219   0.03487   0.02560  -0.0322   1.0000   0.1215
  -3.250  -0.2935   0.03184   0.02179  -0.0313   1.0000   0.1099
  -3.000  -0.2680   0.02874   0.01835  -0.0304   1.0000   0.1059
  -2.750  -0.2408   0.02628   0.01534  -0.0292   1.0000   0.1069
  -2.500  -0.2133   0.02399   0.01259  -0.0281   1.0000   0.1132
  -2.250  -0.1853   0.02194   0.01035  -0.0271   1.0000   0.1312
  -2.000  -0.1547   0.01978   0.00807  -0.0263   1.0000   0.1806
  -1.750  -0.1009   0.01462   0.00535  -0.0290   1.0000   1.0000
  -1.500  -0.0780   0.01461   0.00464  -0.0278   1.0000   1.0000
  -1.250  -0.0554   0.01461   0.00418  -0.0268   1.0000   1.0000
  -1.000  -0.0329   0.01464   0.00383  -0.0258   1.0000   1.0000
  -0.750  -0.0104   0.01468   0.00356  -0.0248   1.0000   1.0000
  -0.500   0.0121   0.01473   0.00332  -0.0238   1.0000   1.0000
  -0.250   0.0344   0.01480   0.00320  -0.0229   1.0000   1.0000
   0.000   0.0568   0.01489   0.00314  -0.0220   1.0000   1.0000
   0.250   0.0792   0.01499   0.00311  -0.0211   1.0000   1.0000
   0.500   0.1015   0.01511   0.00316  -0.0203   1.0000   1.0000
   0.750   0.1237   0.01524   0.00325  -0.0194   1.0000   1.0000
   1.000   0.1459   0.01539   0.00340  -0.0186   1.0000   1.0000
   1.250   0.1680   0.01555   0.00361  -0.0177   1.0000   1.0000
   1.500   0.1899   0.01573   0.00387  -0.0169   1.0000   1.0000
   1.750   0.2119   0.01593   0.00418  -0.0161   1.0000   1.0000
   2.000   0.2336   0.01616   0.00459  -0.0152   1.0000   1.0000
   2.250   0.2553   0.01640   0.00503  -0.0144   1.0000   1.0000
   2.500   0.2768   0.01667   0.00554  -0.0136   1.0000   1.0000
   2.750   0.2982   0.01697   0.00616  -0.0128   1.0000   1.0000
   3.000   0.3193   0.01730   0.00683  -0.0119   1.0000   1.0000
   3.250   0.3402   0.01767   0.00760  -0.0111   1.0000   1.0000
   3.500   0.3611   0.01808   0.00849  -0.0103   1.0000   1.0000
   3.750   0.3817   0.01853   0.00962  -0.0094   1.0000   1.0000
   4.000   0.5878   0.02881   0.01711  -0.0311   0.0935   1.0000
   4.250   0.6166   0.03159   0.02038  -0.0299   0.0899   1.0000
   4.500   0.6440   0.03490   0.02424  -0.0284   0.0943   1.0000
   4.750   0.6696   0.03821   0.02811  -0.0266   0.1007   1.0000
   5.000   0.6927   0.04217   0.03266  -0.0248   0.1108   1.0000
   5.250   0.7170   0.04623   0.03762  -0.0230   0.1349   1.0000
   5.500   0.7587   0.05384   0.04708  -0.0289   0.2792   1.0000
   5.750   0.6807   0.04889   0.04347  -0.0451   0.4409   1.0000
   6.000   0.6367   0.05424   0.04864  -0.0491   0.4748   1.0000
   7.000   0.7524   0.08577   0.07964  -0.0588   0.4549   1.0000
   7.250   0.7505   0.08842   0.08221  -0.0543   0.4064   1.0000
   7.500   0.7636   0.09206   0.08584  -0.0500   0.3610   1.0000
   7.750   0.7878   0.09669   0.09051  -0.0449   0.3175   1.0000
   8.000   0.7703   0.09926   0.09295  -0.0454   0.2996   1.0000
   8.250   0.7875   0.10408   0.09781  -0.0421   0.2716   1.0000
   8.500   0.7810   0.10746   0.10110  -0.0424   0.2560   1.0000
   8.750   0.7782   0.11117   0.10475  -0.0426   0.2407   1.0000
   9.000   0.7805   0.11530   0.10884  -0.0424   0.2262   1.0000
   9.250   0.7872   0.11989   0.11341  -0.0417   0.2120   1.0000
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