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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 50,000
Max Cl/Cd: 22.69 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe10k-il-50000-n5.txt
Download as CSV file: xf-goe10k-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5435   0.09742   0.09065  -0.0114   1.0000   0.0908
  -7.500  -0.5453   0.09475   0.08807  -0.0146   1.0000   0.0942
  -7.250  -0.5486   0.09271   0.08609  -0.0225   1.0000   0.0963
  -7.000  -0.5387   0.08715   0.08057  -0.0184   1.0000   0.0985
  -6.750  -0.5316   0.08326   0.07668  -0.0184   1.0000   0.1010
  -6.500  -0.5248   0.07957   0.07301  -0.0199   1.0000   0.1040
  -6.250  -0.5187   0.07610   0.06948  -0.0252   1.0000   0.1115
  -5.750  -0.4848   0.06543   0.05856  -0.0288   1.0000   0.0618
  -5.500  -0.4649   0.06011   0.05298  -0.0312   1.0000   0.0429
  -5.250  -0.4507   0.05592   0.04864  -0.0318   1.0000   0.0408
  -5.000  -0.4291   0.05116   0.04340  -0.0336   1.0000   0.0367
  -4.750  -0.4121   0.04738   0.03941  -0.0335   1.0000   0.0362
  -4.500  -0.3932   0.04371   0.03542  -0.0335   1.0000   0.0359
  -4.250  -0.3729   0.04016   0.03150  -0.0332   1.0000   0.0354
  -4.000  -0.3514   0.03681   0.02771  -0.0326   1.0000   0.0348
  -3.750  -0.3286   0.03359   0.02396  -0.0319   1.0000   0.0344
  -3.500  -0.3045   0.03067   0.02046  -0.0309   1.0000   0.0349
  -3.250  -0.2788   0.02805   0.01712  -0.0297   1.0000   0.0367
  -3.000  -0.2550   0.02587   0.01470  -0.0288   1.0000   0.0399
  -2.750  -0.2289   0.02389   0.01223  -0.0276   1.0000   0.0437
  -2.500  -0.2026   0.02211   0.01021  -0.0267   1.0000   0.0517
  -2.250  -0.1761   0.02066   0.00837  -0.0257   1.0000   0.0654
  -2.000  -0.1504   0.01913   0.00686  -0.0251   1.0000   0.1017
  -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   0.5068   0.02234   0.00960  -0.0324   0.0615   1.0000
   3.750   0.5340   0.02415   0.01160  -0.0318   0.0466   1.0000
   4.000   0.5645   0.02614   0.01393  -0.0312   0.0395   1.0000
   4.250   0.5943   0.02848   0.01662  -0.0305   0.0346   1.0000
   4.500   0.6226   0.03120   0.01978  -0.0295   0.0330   1.0000
   4.750   0.6473   0.03397   0.02296  -0.0283   0.0311   1.0000
   5.000   0.6688   0.03714   0.02650  -0.0270   0.0293   1.0000
   5.250   0.6895   0.04045   0.03044  -0.0252   0.0289   1.0000
   5.500   0.7075   0.04403   0.03449  -0.0235   0.0292   1.0000
   5.750   0.7235   0.04784   0.03867  -0.0220   0.0296   1.0000
   6.000   0.7393   0.05166   0.04326  -0.0198   0.0313   1.0000
   6.250   0.7513   0.05608   0.04816  -0.0183   0.0330   1.0000
   6.500   0.7611   0.06043   0.05284  -0.0172   0.0345   1.0000
   6.750   0.7693   0.06473   0.05739  -0.0165   0.0358   1.0000
   7.000   0.7764   0.06899   0.06180  -0.0158   0.0371   1.0000
   7.500   0.7825   0.07861   0.07185  -0.0162   0.0435   1.0000
   8.000   0.7117   0.07869   0.07242  -0.0103   0.0458   1.0000
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