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GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 50,000
Max Cl/Cd: 28.72 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe645-il-50000-n5.txt
Download as CSV file: xf-goe645-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2888   0.10498   0.09776  -0.0452   1.0000   0.0855
 -10.250  -0.2915   0.10177   0.09463  -0.0456   1.0000   0.0867
 -10.000  -0.2975   0.09829   0.09125  -0.0462   1.0000   0.0877
  -9.750  -0.3068   0.09464   0.08771  -0.0466   1.0000   0.0886
  -9.500  -0.3196   0.09090   0.08409  -0.0469   1.0000   0.0890
  -9.250  -0.3377   0.08717   0.08051  -0.0467   1.0000   0.0893
  -9.000  -0.3624   0.08374   0.07725  -0.0458   1.0000   0.0893
  -8.750  -0.3954   0.08082   0.07451  -0.0437   1.0000   0.0891
  -8.500  -0.4268   0.07426   0.06805  -0.0478   0.9918   0.0892
  -8.250  -0.4681   0.05543   0.04869  -0.0683   0.9677   0.0901
  -8.000  -0.4706   0.04711   0.03961  -0.0754   0.9513   0.0931
  -7.750  -0.4365   0.04581   0.03832  -0.0779   0.9419   0.0969
  -7.500  -0.4172   0.04240   0.03448  -0.0803   0.9289   0.1011
  -7.250  -0.3959   0.03902   0.03054  -0.0824   0.9170   0.1058
  -7.000  -0.3589   0.03778   0.02931  -0.0848   0.9090   0.1123
  -6.750  -0.3355   0.03553   0.02662  -0.0857   0.8965   0.1200
  -6.500  -0.3026   0.03448   0.02559  -0.0871   0.8870   0.1284
  -6.250  -0.2706   0.03328   0.02429  -0.0885   0.8769   0.1397
  -6.000  -0.2424   0.03239   0.02330  -0.0889   0.8656   0.1526
  -5.750  -0.2065   0.03179   0.02262  -0.0904   0.8568   0.1680
  -5.500  -0.1805   0.03146   0.02218  -0.0901   0.8442   0.1820
  -5.250  -0.1478   0.03114   0.02173  -0.0908   0.8345   0.1972
  -5.000  -0.1187   0.03108   0.02157  -0.0909   0.8230   0.2130
  -4.750  -0.0918   0.03116   0.02157  -0.0905   0.8112   0.2293
  -4.500  -0.0586   0.03068   0.02084  -0.0912   0.8022   0.2445
  -4.250  -0.0342   0.03046   0.02062  -0.0903   0.7894   0.2528
  -4.000  -0.0045   0.02975   0.01963  -0.0905   0.7793   0.2640
  -3.750   0.0238   0.02929   0.01905  -0.0903   0.7684   0.2733
  -3.500   0.0498   0.02886   0.01846  -0.0899   0.7569   0.2839
  -3.250   0.0817   0.02838   0.01770  -0.0902   0.7477   0.2978
  -3.000   0.1048   0.02823   0.01756  -0.0892   0.7353   0.3075
  -2.750   0.1348   0.02786   0.01700  -0.0893   0.7261   0.3199
  -2.500   0.1605   0.02766   0.01666  -0.0887   0.7147   0.3316
  -2.250   0.1869   0.02749   0.01643  -0.0882   0.7042   0.3431
  -2.000   0.2153   0.02728   0.01608  -0.0880   0.6947   0.3565
  -1.750   0.2391   0.02728   0.01595  -0.0872   0.6838   0.3707
  -1.500   0.2687   0.02708   0.01570  -0.0870   0.6753   0.3865
  -1.250   0.2910   0.02715   0.01576  -0.0860   0.6641   0.4011
  -1.000   0.3221   0.02693   0.01546  -0.0861   0.6565   0.4177
  -0.750   0.3440   0.02704   0.01555  -0.0852   0.6453   0.4306
  -0.500   0.3760   0.02681   0.01519  -0.0854   0.6380   0.4451
  -0.250   0.3975   0.02697   0.01538  -0.0844   0.6272   0.4579
   0.000   0.4282   0.02677   0.01512  -0.0844   0.6198   0.4729
   0.250   0.4498   0.02692   0.01533  -0.0835   0.6094   0.4880
   0.500   0.4795   0.02675   0.01514  -0.0833   0.6021   0.5077
   0.750   0.5007   0.02690   0.01538  -0.0823   0.5919   0.5288
   1.000   0.5294   0.02666   0.01520  -0.0819   0.5845   0.5594
   1.250   0.5493   0.02670   0.01547  -0.0806   0.5746   0.6008
   1.500   0.5778   0.02604   0.01532  -0.0796   0.5673   0.7083
   1.750   0.6290   0.02604   0.01545  -0.0840   0.5556   1.0000
   2.000   0.6537   0.02634   0.01553  -0.0834   0.5472   1.0000
   2.250   0.6766   0.02671   0.01572  -0.0825   0.5381   1.0000
   2.500   0.7008   0.02704   0.01589  -0.0818   0.5301   1.0000
   2.750   0.7222   0.02748   0.01621  -0.0807   0.5212   1.0000
   3.000   0.7478   0.02778   0.01634  -0.0801   0.5139   1.0000
   3.250   0.7662   0.02837   0.01689  -0.0788   0.5049   1.0000
   3.500   0.7960   0.02851   0.01683  -0.0787   0.4988   1.0000
   3.750   0.8088   0.02938   0.01775  -0.0767   0.4894   1.0000
   4.000   0.8360   0.02965   0.01788  -0.0763   0.4829   1.0000
   4.250   0.8515   0.03045   0.01870  -0.0747   0.4748   1.0000
   4.500   0.8737   0.03096   0.01914  -0.0738   0.4677   1.0000
   4.750   0.8980   0.03141   0.01952  -0.0731   0.4616   1.0000
   5.000   0.9101   0.03239   0.02056  -0.0712   0.4533   1.0000
   5.250   0.9376   0.03268   0.02075  -0.0709   0.4476   1.0000
   5.500   0.9480   0.03378   0.02192  -0.0688   0.4398   1.0000
   5.750   0.9671   0.03445   0.02257  -0.0676   0.4330   1.0000
   6.000   0.9959   0.03468   0.02270  -0.0675   0.4278   1.0000
   6.250   0.9957   0.03629   0.02448  -0.0644   0.4195   1.0000
   6.500   1.0200   0.03670   0.02484  -0.0638   0.4138   1.0000
   6.750   1.0335   0.03771   0.02588  -0.0622   0.4078   1.0000
   7.000   1.0356   0.03923   0.02749  -0.0595   0.4006   1.0000
   7.250   1.0647   0.03936   0.02756  -0.0593   0.3956   1.0000
   7.500   1.0568   0.04133   0.02965  -0.0557   0.3887   1.0000
   7.750   1.0592   0.04276   0.03113  -0.0531   0.3823   1.0000
   8.000   1.1004   0.04212   0.03040  -0.0538   0.3775   1.0000
   8.250   1.0526   0.04669   0.03518  -0.0480   0.3696   1.0000
   8.500   1.0661   0.04765   0.03616  -0.0468   0.3642   1.0000
   8.750   1.1117   0.04650   0.03495  -0.0472   0.3607   1.0000
   9.000   1.0065   0.05774   0.04648  -0.0433   0.3494   1.0000
   9.250   1.0425   0.05661   0.04534  -0.0424   0.3463   1.0000
   9.750   0.9900   0.06824   0.05714  -0.0423   0.3302   1.0000
  10.250   0.9569   0.07919   0.06822  -0.0437   0.3144   1.0000
  10.500   0.9217   0.08752   0.07662  -0.0457   0.3026   1.0000
  10.750   0.9473   0.08692   0.07605  -0.0445   0.2991   1.0000
  11.000   0.9781   0.08550   0.07466  -0.0429   0.2970   1.0000
  11.500   0.9401   0.09799   0.08730  -0.0459   0.2787   1.0000
  12.000   0.9528   0.10268   0.09211  -0.0460   0.2665   1.0000
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