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GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 619 AIRFOIL (goe619-il)
Reynolds number: 200,000
Max Cl/Cd: 73.74 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe619-il-200000.txt
Download as CSV file: xf-goe619-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 619 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2039   0.09976   0.09650  -0.0473   0.9878   0.0893
  -9.500  -0.5675   0.04796   0.04392  -0.0871   0.9786   0.0565
  -9.250  -0.5631   0.04014   0.03536  -0.0945   0.9698   0.0567
  -9.000  -0.5517   0.03579   0.03057  -0.0962   0.9605   0.0573
  -8.750  -0.5224   0.03281   0.02733  -0.0991   0.9566   0.0580
  -8.500  -0.5001   0.03089   0.02522  -0.0996   0.9488   0.0587
  -8.250  -0.4691   0.02906   0.02317  -0.1015   0.9442   0.0597
  -8.000  -0.4331   0.02737   0.02123  -0.1041   0.9414   0.0612
  -7.750  -0.4102   0.02608   0.01972  -0.1038   0.9330   0.0627
  -7.500  -0.3758   0.02455   0.01786  -0.1056   0.9290   0.0644
  -7.250  -0.3379   0.02291   0.01601  -0.1080   0.9267   0.0661
  -7.000  -0.3094   0.02205   0.01516  -0.1083   0.9203   0.0679
  -6.750  -0.2752   0.02121   0.01424  -0.1096   0.9154   0.0705
  -6.500  -0.2357   0.02032   0.01314  -0.1118   0.9124   0.0742
  -6.250  -0.1962   0.01934   0.01222  -0.1142   0.9099   0.0788
  -6.000  -0.1716   0.01890   0.01166  -0.1134   0.9013   0.0841
  -5.750  -0.1370   0.01806   0.01086  -0.1148   0.8967   0.0924
  -5.500  -0.0992   0.01729   0.01005  -0.1166   0.8933   0.1066
  -5.250  -0.0762   0.01688   0.00964  -0.1157   0.8841   0.1178
  -5.000  -0.0424   0.01643   0.00913  -0.1167   0.8790   0.1292
  -4.750  -0.0100   0.01617   0.00879  -0.1174   0.8733   0.1384
  -4.500   0.0154   0.01582   0.00846  -0.1168   0.8649   0.1455
  -4.250   0.0500   0.01553   0.00808  -0.1179   0.8600   0.1538
  -4.000   0.0735   0.01534   0.00793  -0.1169   0.8511   0.1616
  -3.750   0.1046   0.01513   0.00763  -0.1172   0.8448   0.1708
  -3.500   0.1320   0.01494   0.00750  -0.1170   0.8378   0.1809
  -3.250   0.1586   0.01475   0.00732  -0.1165   0.8300   0.1918
  -3.000   0.1912   0.01449   0.00703  -0.1171   0.8248   0.2059
  -2.750   0.2130   0.01439   0.00696  -0.1157   0.8153   0.2210
  -2.500   0.2435   0.01415   0.00676  -0.1159   0.8092   0.2424
  -2.250   0.2673   0.01410   0.00676  -0.1149   0.8005   0.2644
  -2.000   0.2965   0.01400   0.00660  -0.1148   0.7932   0.2861
  -1.750   0.3215   0.01393   0.00654  -0.1139   0.7841   0.3031
  -1.500   0.3506   0.01376   0.00634  -0.1137   0.7755   0.3189
  -1.250   0.3747   0.01365   0.00624  -0.1126   0.7648   0.3325
  -1.000   0.4043   0.01349   0.00602  -0.1124   0.7562   0.3471
  -0.750   0.4280   0.01342   0.00596  -0.1113   0.7458   0.3612
  -0.500   0.4567   0.01334   0.00585  -0.1112   0.7387   0.3769
  -0.250   0.4808   0.01328   0.00585  -0.1102   0.7295   0.3917
   0.000   0.5097   0.01319   0.00574  -0.1101   0.7225   0.4087
   0.250   0.5330   0.01314   0.00576  -0.1090   0.7128   0.4280
   0.500   0.5608   0.01302   0.00567  -0.1086   0.7053   0.4512
   0.750   0.5840   0.01292   0.00568  -0.1075   0.6955   0.4778
   1.000   0.6105   0.01272   0.00559  -0.1069   0.6878   0.5133
   1.250   0.6313   0.01239   0.00559  -0.1053   0.6780   0.5708
   1.500   0.7104   0.01147   0.00558  -0.1151   0.6665   1.0000
   1.750   0.7352   0.01155   0.00549  -0.1142   0.6565   1.0000
   2.000   0.7565   0.01164   0.00553  -0.1127   0.6448   1.0000
   2.250   0.7798   0.01173   0.00552  -0.1115   0.6338   1.0000
   2.500   0.8036   0.01183   0.00550  -0.1104   0.6224   1.0000
   2.750   0.8246   0.01193   0.00556  -0.1088   0.6093   1.0000
   3.000   0.8464   0.01204   0.00561  -0.1074   0.5956   1.0000
   3.250   0.8681   0.01216   0.00565  -0.1059   0.5810   1.0000
   3.500   0.8891   0.01229   0.00571  -0.1043   0.5646   1.0000
   3.750   0.9092   0.01243   0.00577  -0.1025   0.5461   1.0000
   4.000   0.9285   0.01261   0.00584  -0.1006   0.5255   1.0000
   4.250   0.9468   0.01284   0.00595  -0.0986   0.5028   1.0000
   4.500   0.9640   0.01313   0.00610  -0.0963   0.4777   1.0000
   4.750   0.9802   0.01350   0.00629  -0.0940   0.4525   1.0000
   5.000   0.9960   0.01393   0.00656  -0.0916   0.4283   1.0000
   5.250   1.0116   0.01442   0.00686  -0.0893   0.4073   1.0000
   5.500   1.0281   0.01491   0.00720  -0.0872   0.3892   1.0000
   6.000   1.0620   0.01585   0.00794  -0.0832   0.3589   1.0000
   6.250   1.0800   0.01629   0.00832  -0.0815   0.3469   1.0000
   6.500   1.0980   0.01678   0.00872  -0.0798   0.3368   1.0000
   6.750   1.1160   0.01721   0.00911  -0.0781   0.3279   1.0000
   7.000   1.1346   0.01769   0.00954  -0.0765   0.3202   1.0000
   7.250   1.1527   0.01811   0.00995  -0.0748   0.3128   1.0000
   7.500   1.1726   0.01865   0.01039  -0.0735   0.3065   1.0000
   7.750   1.1903   0.01903   0.01084  -0.0718   0.3002   1.0000
   8.000   1.2088   0.01950   0.01129  -0.0703   0.2944   1.0000
   8.250   1.2286   0.02002   0.01178  -0.0691   0.2889   1.0000
   8.500   1.2462   0.02044   0.01227  -0.0674   0.2838   1.0000
   8.750   1.2646   0.02091   0.01275  -0.0660   0.2789   1.0000
   9.000   1.2860   0.02149   0.01327  -0.0652   0.2742   1.0000
   9.250   1.3010   0.02192   0.01382  -0.0632   0.2693   1.0000
   9.500   1.3165   0.02238   0.01432  -0.0614   0.2643   1.0000
   9.750   1.3342   0.02298   0.01484  -0.0600   0.2585   1.0000
  10.000   1.3438   0.02344   0.01546  -0.0574   0.2527   1.0000
  10.250   1.3552   0.02398   0.01602  -0.0552   0.2467   1.0000
  10.500   1.3679   0.02461   0.01666  -0.0533   0.2408   1.0000
  10.750   1.3772   0.02521   0.01738  -0.0510   0.2346   1.0000
  11.000   1.3879   0.02592   0.01808  -0.0490   0.2288   1.0000
  11.250   1.3992   0.02664   0.01890  -0.0472   0.2236   1.0000
  11.500   1.4082   0.02742   0.01978  -0.0452   0.2173   1.0000
  11.750   1.4163   0.02836   0.02069  -0.0433   0.2110   1.0000
  12.000   1.4261   0.02922   0.02173  -0.0416   0.2046   1.0000
  12.250   1.4331   0.03031   0.02284  -0.0399   0.1981   1.0000
  12.500   1.4423   0.03134   0.02400  -0.0384   0.1910   1.0000
  12.750   1.4481   0.03262   0.02533  -0.0368   0.1833   1.0000
  13.000   1.4559   0.03388   0.02669  -0.0355   0.1736   1.0000
  13.250   1.4608   0.03540   0.02827  -0.0342   0.1629   1.0000
  13.500   1.4638   0.03715   0.03004  -0.0329   0.1498   1.0000
  13.750   1.4627   0.03935   0.03220  -0.0316   0.1331   1.0000
  14.000   1.4581   0.04198   0.03476  -0.0304   0.1186   1.0000
  14.250   1.4534   0.04477   0.03751  -0.0294   0.1076   1.0000
  14.500   1.4493   0.04762   0.04037  -0.0286   0.1003   1.0000
  14.750   1.4453   0.05058   0.04336  -0.0280   0.0946   1.0000
  15.000   1.4416   0.05362   0.04647  -0.0276   0.0908   1.0000
  15.250   1.4399   0.05654   0.04947  -0.0273   0.0874   1.0000
  15.500   1.4357   0.05986   0.05285  -0.0273   0.0845   1.0000
  15.750   1.4290   0.06357   0.05664  -0.0275   0.0820   1.0000
  16.000   1.4260   0.06695   0.06011  -0.0277   0.0799   1.0000
  16.250   1.4233   0.07039   0.06367  -0.0282   0.0778   1.0000
  16.500   1.4165   0.07446   0.06783  -0.0289   0.0752   1.0000
  16.750   1.4080   0.07887   0.07232  -0.0298   0.0733   1.0000
  17.250   1.3929   0.08780   0.08146  -0.0322   0.0698   1.0000
  17.500   1.3874   0.09210   0.08590  -0.0334   0.0681   1.0000
  17.750   1.3800   0.09675   0.09068  -0.0350   0.0665   1.0000
  18.000   1.3715   0.10166   0.09568  -0.0367   0.0650   1.0000
  18.250   1.3625   0.10671   0.10081  -0.0386   0.0637   1.0000
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