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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 500,000
Max Cl/Cd: 80.67 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe565-il-500000-n5.txt
Download as CSV file: xf-goe565-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.8329   0.03729   0.03454  -0.0684   1.0000   0.0069
 -11.000  -0.8432   0.03266   0.02958  -0.0678   1.0000   0.0070
 -10.750  -0.8431   0.02971   0.02636  -0.0662   1.0000   0.0071
 -10.500  -0.8294   0.02717   0.02354  -0.0664   0.9989   0.0074
 -10.250  -0.8028   0.02491   0.02097  -0.0685   0.9961   0.0077
 -10.000  -0.7755   0.02313   0.01891  -0.0702   0.9934   0.0079
  -9.750  -0.7504   0.02115   0.01670  -0.0714   0.9902   0.0085
  -9.500  -0.7228   0.01985   0.01522  -0.0725   0.9880   0.0089
  -9.250  -0.6939   0.01870   0.01389  -0.0736   0.9863   0.0094
  -9.000  -0.6674   0.01773   0.01273  -0.0740   0.9834   0.0099
  -8.750  -0.6394   0.01682   0.01165  -0.0746   0.9809   0.0105
  -8.500  -0.6100   0.01603   0.01068  -0.0754   0.9790   0.0111
  -8.250  -0.5799   0.01511   0.00964  -0.0764   0.9774   0.0122
  -8.000  -0.5518   0.01445   0.00890  -0.0768   0.9747   0.0137
  -7.750  -0.5231   0.01387   0.00821  -0.0772   0.9719   0.0152
  -7.500  -0.4927   0.01333   0.00760  -0.0780   0.9700   0.0176
  -7.250  -0.4615   0.01293   0.00715  -0.0789   0.9683   0.0204
  -7.000  -0.4296   0.01268   0.00690  -0.0798   0.9667   0.0235
  -6.750  -0.4019   0.01254   0.00671  -0.0798   0.9626   0.0267
  -6.500  -0.3716   0.01228   0.00639  -0.0804   0.9598   0.0289
  -6.250  -0.3400   0.01216   0.00626  -0.0812   0.9576   0.0310
  -6.000  -0.3098   0.01206   0.00613  -0.0817   0.9548   0.0332
  -5.750  -0.2816   0.01190   0.00590  -0.0818   0.9506   0.0349
  -5.500  -0.2512   0.01178   0.00572  -0.0823   0.9473   0.0360
  -5.250  -0.2219   0.01124   0.00515  -0.0827   0.9442   0.0382
  -5.000  -0.1950   0.01108   0.00498  -0.0825   0.9390   0.0401
  -4.750  -0.1661   0.01082   0.00467  -0.0827   0.9351   0.0416
  -4.500  -0.1376   0.01050   0.00430  -0.0828   0.9305   0.0426
  -4.250  -0.1107   0.01021   0.00395  -0.0825   0.9235   0.0436
  -4.000  -0.0822   0.00994   0.00362  -0.0825   0.9175   0.0446
  -3.750  -0.0555   0.00973   0.00336  -0.0822   0.9095   0.0454
  -3.500  -0.0276   0.00957   0.00314  -0.0820   0.9022   0.0462
  -3.250  -0.0013   0.00920   0.00273  -0.0816   0.8937   0.0482
  -3.000   0.0259   0.00897   0.00246  -0.0814   0.8868   0.0500
  -2.750   0.0529   0.00878   0.00225  -0.0811   0.8791   0.0518
  -2.500   0.0802   0.00863   0.00206  -0.0809   0.8715   0.0538
  -2.250   0.1074   0.00850   0.00189  -0.0806   0.8620   0.0558
  -2.000   0.1341   0.00839   0.00172  -0.0801   0.8480   0.0579
  -1.750   0.1607   0.00830   0.00156  -0.0796   0.8298   0.0613
  -1.500   0.1868   0.00819   0.00143  -0.0791   0.8089   0.0696
  -1.250   0.2130   0.00807   0.00135  -0.0786   0.7909   0.0979
  -1.000   0.2395   0.00798   0.00126  -0.0782   0.7765   0.1177
  -0.750   0.2657   0.00784   0.00119  -0.0778   0.7629   0.1501
  -0.500   0.2909   0.00757   0.00117  -0.0774   0.7487   0.2529
   0.000   0.3429   0.00745   0.00115  -0.0764   0.7174   0.3294
   0.250   0.3679   0.00731   0.00116  -0.0759   0.6994   0.3970
   0.500   0.3922   0.00709   0.00121  -0.0752   0.6816   0.5033
   0.750   0.4168   0.00697   0.00127  -0.0744   0.6637   0.5823
   1.000   0.4415   0.00690   0.00132  -0.0737   0.6433   0.6441
   1.250   0.4654   0.00688   0.00136  -0.0727   0.6167   0.6951
   1.750   0.5437   0.00674   0.00155  -0.0774   0.5348   1.0000
   2.000   0.5660   0.00703   0.00166  -0.0763   0.4985   1.0000
   2.250   0.5883   0.00736   0.00179  -0.0751   0.4554   1.0000
   2.500   0.6101   0.00775   0.00193  -0.0740   0.4025   1.0000
   2.750   0.6329   0.00809   0.00208  -0.0730   0.3621   1.0000
   3.000   0.6565   0.00838   0.00223  -0.0721   0.3330   1.0000
   3.250   0.6805   0.00866   0.00240  -0.0714   0.3062   1.0000
   3.500   0.7041   0.00898   0.00258  -0.0706   0.2749   1.0000
   3.750   0.7270   0.00937   0.00278  -0.0697   0.2335   1.0000
   4.000   0.7497   0.00980   0.00302  -0.0688   0.1950   1.0000
   4.250   0.7737   0.01010   0.00324  -0.0681   0.1781   1.0000
   4.500   0.7982   0.01036   0.00347  -0.0674   0.1672   1.0000
   4.750   0.8223   0.01066   0.00371  -0.0667   0.1546   1.0000
   5.000   0.8468   0.01092   0.00395  -0.0661   0.1439   1.0000
   5.250   0.8714   0.01116   0.00419  -0.0655   0.1333   1.0000
   5.500   0.8951   0.01150   0.00445  -0.0648   0.1132   1.0000
   5.750   0.9164   0.01209   0.00483  -0.0637   0.0774   1.0000
   6.000   0.9373   0.01271   0.00530  -0.0626   0.0476   1.0000
   6.250   0.9600   0.01316   0.00571  -0.0617   0.0390   1.0000
   6.500   0.9834   0.01352   0.00610  -0.0609   0.0359   1.0000
   6.750   1.0061   0.01395   0.00653  -0.0600   0.0329   1.0000
   7.000   1.0283   0.01443   0.00706  -0.0591   0.0299   1.0000
   7.250   1.0515   0.01478   0.00746  -0.0583   0.0285   1.0000
   7.500   1.0745   0.01513   0.00787  -0.0575   0.0267   1.0000
   7.750   1.0969   0.01554   0.00832  -0.0566   0.0245   1.0000
   8.000   1.1181   0.01606   0.00886  -0.0556   0.0220   1.0000
   8.250   1.1395   0.01654   0.00939  -0.0545   0.0201   1.0000
   8.500   1.1615   0.01694   0.00986  -0.0536   0.0183   1.0000
   8.750   1.1827   0.01740   0.01033  -0.0526   0.0160   1.0000
   9.000   1.2023   0.01800   0.01095  -0.0514   0.0143   1.0000
   9.250   1.2222   0.01854   0.01155  -0.0502   0.0131   1.0000
   9.500   1.2412   0.01912   0.01219  -0.0488   0.0121   1.0000
   9.750   1.2592   0.01978   0.01287  -0.0474   0.0110   1.0000
  10.000   1.2749   0.02060   0.01375  -0.0456   0.0102   1.0000
  10.250   1.2915   0.02127   0.01454  -0.0440   0.0096   1.0000
  10.500   1.3064   0.02194   0.01529  -0.0420   0.0090   1.0000
  10.750   1.3191   0.02270   0.01613  -0.0398   0.0086   1.0000
  11.000   1.3311   0.02349   0.01700  -0.0375   0.0081   1.0000
  11.250   1.3414   0.02440   0.01798  -0.0351   0.0077   1.0000
  11.500   1.3467   0.02567   0.01935  -0.0322   0.0073   1.0000
  11.750   1.3555   0.02670   0.02049  -0.0299   0.0071   1.0000
  12.000   1.3637   0.02781   0.02172  -0.0276   0.0069   1.0000
  12.250   1.3696   0.02911   0.02316  -0.0253   0.0068   1.0000
  12.500   1.3749   0.03050   0.02468  -0.0231   0.0066   1.0000
  12.750   1.3798   0.03197   0.02627  -0.0212   0.0064   1.0000
  13.000   1.3834   0.03361   0.02803  -0.0193   0.0062   1.0000
  13.250   1.3877   0.03525   0.02978  -0.0178   0.0060   1.0000
  13.500   1.3920   0.03697   0.03160  -0.0165   0.0058   1.0000
  13.750   1.3927   0.03911   0.03387  -0.0152   0.0056   1.0000
  14.000   1.3880   0.04195   0.03686  -0.0142   0.0056   1.0000
  14.250   1.3872   0.04454   0.03955  -0.0137   0.0054   1.0000
  14.500   1.3813   0.04789   0.04304  -0.0136   0.0053   1.0000
  14.750   1.3734   0.05171   0.04700  -0.0139   0.0052   1.0000
  15.000   1.3614   0.05637   0.05181  -0.0149   0.0052   1.0000
  15.250   1.3507   0.06122   0.05682  -0.0164   0.0051   1.0000
  15.500   1.3416   0.06618   0.06195  -0.0184   0.0051   1.0000
  15.750   1.3319   0.07158   0.06752  -0.0208   0.0050   1.0000
  16.000   1.3155   0.07834   0.07443  -0.0241   0.0051   1.0000
  16.250   1.3020   0.08501   0.08129  -0.0276   0.0050   1.0000
  16.500   1.2829   0.09295   0.08938  -0.0318   0.0050   1.0000
  16.750   1.2669   0.10058   0.09717  -0.0360   0.0050   1.0000
  17.000   1.2476   0.10906   0.10579  -0.0406   0.0050   1.0000
  17.250   1.2293   0.11765   0.11450  -0.0455   0.0050   1.0000
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