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GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 723 AIRFOIL (goe723-il)
Reynolds number: 50,000
Max Cl/Cd: 33.41 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe723-il-50000-n5.txt
Download as CSV file: xf-goe723-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 723 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3477   0.09577   0.08880  -0.0441   1.0000   0.0869
  -8.000  -0.3466   0.09367   0.08679  -0.0418   1.0000   0.0861
  -7.750  -0.3542   0.09196   0.08519  -0.0392   1.0000   0.0852
  -7.500  -0.3687   0.09057   0.08394  -0.0362   1.0000   0.0843
  -7.250  -0.3841   0.08909   0.08259  -0.0336   1.0000   0.0833
  -6.750  -0.3646   0.07134   0.06461  -0.0587   0.9750   0.0744
  -6.500  -0.3439   0.06643   0.05959  -0.0642   0.9644   0.0735
  -6.250  -0.3242   0.06087   0.05383  -0.0706   0.9533   0.0726
  -6.000  -0.3027   0.05492   0.04756  -0.0774   0.9429   0.0716
  -5.750  -0.2780   0.04935   0.04151  -0.0836   0.9334   0.0714
  -5.500  -0.2550   0.04524   0.03690  -0.0871   0.9231   0.0721
  -5.250  -0.2226   0.04148   0.03251  -0.0911   0.9165   0.0730
  -5.000  -0.1983   0.03892   0.02946  -0.0923   0.9064   0.0735
  -4.750  -0.1633   0.03640   0.02643  -0.0948   0.9007   0.0738
  -4.500  -0.1376   0.03471   0.02435  -0.0952   0.8914   0.0742
  -4.250  -0.1024   0.03300   0.02227  -0.0969   0.8854   0.0748
  -4.000  -0.0739   0.03168   0.02081  -0.0974   0.8774   0.0759
  -3.750  -0.0427   0.03059   0.01960  -0.0982   0.8702   0.0779
  -3.500  -0.0087   0.02961   0.01845  -0.0994   0.8645   0.0812
  -3.250   0.0160   0.02894   0.01761  -0.0989   0.8550   0.0843
  -3.000   0.0520   0.02808   0.01654  -0.1001   0.8497   0.0872
  -2.750   0.0750   0.02754   0.01599  -0.0994   0.8403   0.0900
  -2.500   0.1083   0.02689   0.01524  -0.1003   0.8342   0.0946
  -1.750   0.2019   0.02517   0.01370  -0.1024   0.8133   0.1629
  -1.500   0.2266   0.02482   0.01382  -0.1022   0.8044   0.2812
  -1.250   0.2586   0.02466   0.01396  -0.1026   0.7989   0.3992
  -1.000   0.2768   0.02490   0.01435  -0.1008   0.7895   0.4640
  -0.750   0.3047   0.02480   0.01441  -0.1002   0.7834   0.5323
  -0.500   0.3265   0.02484   0.01454  -0.0989   0.7751   0.5784
  -0.250   0.3560   0.02467   0.01441  -0.0989   0.7685   0.6183
   0.000   0.3866   0.02440   0.01424  -0.0990   0.7623   0.6660
   0.250   0.4133   0.02415   0.01428  -0.0986   0.7541   0.7429
   0.500   0.4729   0.02366   0.01383  -0.1045   0.7491   1.0000
   0.750   0.4945   0.02417   0.01412  -0.1037   0.7396   1.0000
   1.000   0.5266   0.02432   0.01405  -0.1043   0.7332   1.0000
   1.250   0.5486   0.02480   0.01437  -0.1035   0.7240   1.0000
   1.500   0.5786   0.02498   0.01439  -0.1036   0.7169   1.0000
   1.750   0.6012   0.02543   0.01473  -0.1027   0.7079   1.0000
   2.000   0.6297   0.02564   0.01482  -0.1026   0.7003   1.0000
   2.250   0.6523   0.02608   0.01518  -0.1017   0.6914   1.0000
   2.500   0.6797   0.02632   0.01535  -0.1014   0.6836   1.0000
   2.750   0.7020   0.02679   0.01577  -0.1004   0.6748   1.0000
   3.000   0.7283   0.02708   0.01601  -0.0999   0.6669   1.0000
   3.250   0.7505   0.02756   0.01648  -0.0990   0.6582   1.0000
   3.500   0.7759   0.02789   0.01679  -0.0984   0.6502   1.0000
   3.750   0.7976   0.02841   0.01732  -0.0973   0.6416   1.0000
   4.000   0.8224   0.02876   0.01768  -0.0966   0.6335   1.0000
   4.250   0.8430   0.02933   0.01828  -0.0955   0.6246   1.0000
   4.500   0.8681   0.02968   0.01866  -0.0948   0.6167   1.0000
   4.750   0.8870   0.03034   0.01938  -0.0935   0.6075   1.0000
   5.000   0.9129   0.03065   0.01973  -0.0929   0.5998   1.0000
   5.250   0.9295   0.03144   0.02060  -0.0913   0.5904   1.0000
   5.500   0.9564   0.03171   0.02093  -0.0908   0.5830   1.0000
   5.750   0.9705   0.03264   0.02198  -0.0890   0.5731   1.0000
   6.000   0.9985   0.03287   0.02228  -0.0886   0.5662   1.0000
   6.250   1.0097   0.03397   0.02351  -0.0865   0.5560   1.0000
   6.500   1.0401   0.03403   0.02367  -0.0862   0.5493   1.0000
   6.750   1.0501   0.03499   0.02476  -0.0838   0.5374   1.0000
   7.000   1.0725   0.03495   0.02481  -0.0822   0.5251   1.0000
   7.250   1.0958   0.03444   0.02437  -0.0803   0.5094   1.0000
   7.500   1.1137   0.03412   0.02411  -0.0777   0.4918   1.0000
   7.750   1.1285   0.03403   0.02408  -0.0750   0.4740   1.0000
   8.000   1.1406   0.03414   0.02424  -0.0721   0.4562   1.0000
   8.250   1.1497   0.03453   0.02472  -0.0690   0.4396   1.0000
   8.500   1.1581   0.03498   0.02525  -0.0659   0.4218   1.0000
   8.750   1.1654   0.03549   0.02579  -0.0629   0.4012   1.0000
   9.000   1.1666   0.03655   0.02692  -0.0597   0.3781   1.0000
   9.250   1.1715   0.03744   0.02780  -0.0570   0.3525   1.0000
   9.500   1.1739   0.03869   0.02900  -0.0543   0.3233   1.0000
   9.750   1.1711   0.04056   0.03084  -0.0518   0.2873   1.0000
  10.000   1.1655   0.04288   0.03296  -0.0495   0.2394   1.0000
  10.250   1.1560   0.04579   0.03548  -0.0475   0.1927   1.0000
  10.500   1.1456   0.04913   0.03847  -0.0459   0.1664   1.0000
  10.750   1.1383   0.05239   0.04154  -0.0447   0.1516   1.0000
  11.000   1.1331   0.05556   0.04455  -0.0437   0.1422   1.0000
  11.250   1.1324   0.05836   0.04734  -0.0427   0.1343   1.0000
  11.500   1.1317   0.06114   0.04998  -0.0417   0.1284   1.0000
  11.750   1.1366   0.06342   0.05236  -0.0408   0.1221   1.0000
  12.000   1.1419   0.06562   0.05458  -0.0398   0.1168   1.0000
  12.250   1.1518   0.06735   0.05628  -0.0385   0.1124   1.0000
  12.500   1.1644   0.06895   0.05806  -0.0374   0.1081   1.0000
  12.750   1.1778   0.07049   0.05966  -0.0362   0.1035   1.0000
  13.000   1.2010   0.07109   0.06015  -0.0345   0.0987   1.0000
  13.250   1.2139   0.07302   0.06242  -0.0336   0.0953   1.0000
  13.500   1.2272   0.07495   0.06456  -0.0328   0.0916   1.0000
  13.750   1.2441   0.07648   0.06615  -0.0318   0.0877   1.0000
  14.000   1.2604   0.07841   0.06818  -0.0309   0.0844   1.0000
  14.250   1.2599   0.08187   0.07197  -0.0308   0.0821   1.0000
  14.500   1.2586   0.08542   0.07580  -0.0308   0.0796   1.0000
  14.750   1.2601   0.08865   0.07920  -0.0309   0.0772   1.0000
  15.000   1.2791   0.09021   0.08070  -0.0300   0.0742   1.0000
  15.250   1.2626   0.09554   0.08636  -0.0312   0.0733   1.0000
  15.500   1.2443   0.10142   0.09258  -0.0330   0.0724   1.0000
  15.750   1.2231   0.10810   0.09956  -0.0356   0.0717   1.0000
  16.000   1.1993   0.11569   0.10742  -0.0391   0.0713   1.0000
  16.250   1.1699   0.12492   0.11691  -0.0441   0.0712   1.0000
  16.500   1.1339   0.13657   0.12877  -0.0511   0.0716   1.0000
  16.750   1.0916   0.15166   0.14400  -0.0606   0.0722   1.0000
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