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GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 623 AIRFOIL (goe623-il)
Reynolds number: 100,000
Max Cl/Cd: 55.04 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe623-il-100000-n5.txt
Download as CSV file: xf-goe623-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 623 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3968   0.09178   0.08678  -0.0447   1.0000   0.0398
  -9.500  -0.4014   0.08724   0.08230  -0.0465   1.0000   0.0397
  -9.250  -0.4096   0.08257   0.07770  -0.0483   1.0000   0.0396
  -9.000  -0.4231   0.07808   0.07332  -0.0495   1.0000   0.0395
  -8.750  -0.4446   0.07431   0.06968  -0.0495   1.0000   0.0393
  -8.500  -0.4682   0.07003   0.06549  -0.0499   1.0000   0.0391
  -8.250  -0.4917   0.06410   0.05954  -0.0513   0.9990   0.0389
  -8.000  -0.5001   0.04887   0.04350  -0.0645   0.9858   0.0395
  -7.750  -0.4856   0.04295   0.03703  -0.0685   0.9772   0.0408
  -7.500  -0.4607   0.03999   0.03380  -0.0708   0.9707   0.0420
  -7.250  -0.4354   0.03660   0.02999  -0.0731   0.9640   0.0431
  -7.000  -0.4085   0.03395   0.02692  -0.0748   0.9574   0.0451
  -6.750  -0.3799   0.03112   0.02349  -0.0764   0.9512   0.0472
  -6.500  -0.3481   0.02868   0.02046  -0.0780   0.9462   0.0484
  -6.250  -0.3201   0.02701   0.01861  -0.0787   0.9386   0.0499
  -6.000  -0.2863   0.02589   0.01738  -0.0804   0.9337   0.0524
  -5.750  -0.2578   0.02474   0.01601  -0.0807   0.9258   0.0544
  -5.500  -0.2253   0.02350   0.01453  -0.0817   0.9197   0.0562
  -5.250  -0.1942   0.02246   0.01328  -0.0823   0.9129   0.0580
  -5.000  -0.1645   0.02155   0.01233  -0.0828   0.9052   0.0607
  -4.750  -0.1329   0.02082   0.01154  -0.0836   0.8987   0.0645
  -4.500  -0.1047   0.02014   0.01074  -0.0835   0.8898   0.0680
  -4.250  -0.0744   0.01938   0.00993  -0.0839   0.8826   0.0721
  -4.000  -0.0470   0.01879   0.00930  -0.0838   0.8733   0.0784
  -3.750  -0.0186   0.01819   0.00874  -0.0838   0.8649   0.0897
  -3.500   0.0097   0.01773   0.00840  -0.0838   0.8560   0.1132
  -3.250   0.0373   0.01745   0.00810  -0.0836   0.8464   0.1431
  -3.000   0.0666   0.01716   0.00772  -0.0836   0.8383   0.1667
  -2.750   0.0925   0.01688   0.00750  -0.0832   0.8274   0.1889
  -2.500   0.1202   0.01657   0.00726  -0.0831   0.8185   0.2191
  -2.250   0.1470   0.01628   0.00708  -0.0828   0.8085   0.2525
  -2.000   0.1733   0.01599   0.00690  -0.0825   0.7984   0.2927
  -1.750   0.2008   0.01557   0.00667  -0.0822   0.7899   0.3512
  -1.500   0.2252   0.01511   0.00658  -0.0816   0.7788   0.4493
  -1.250   0.2476   0.01448   0.00654  -0.0801   0.7696   0.6144
  -1.000   0.2715   0.01401   0.00657  -0.0779   0.7605   0.7975
  -0.750   0.3168   0.01389   0.00649  -0.0805   0.7511   0.9274
  -0.500   0.3667   0.01383   0.00624  -0.0848   0.7429   0.9906
  -0.250   0.3969   0.01390   0.00617  -0.0854   0.7322   1.0000
   0.000   0.4219   0.01397   0.00608  -0.0847   0.7229   1.0000
   0.250   0.4471   0.01405   0.00601  -0.0841   0.7135   1.0000
   0.500   0.4719   0.01416   0.00600  -0.0835   0.7035   1.0000
   0.750   0.4976   0.01424   0.00594  -0.0829   0.6939   1.0000
   1.000   0.5228   0.01433   0.00591  -0.0823   0.6830   1.0000
   1.250   0.5478   0.01445   0.00592  -0.0816   0.6717   1.0000
   1.500   0.5735   0.01456   0.00591  -0.0810   0.6613   1.0000
   1.750   0.5993   0.01467   0.00591  -0.0805   0.6507   1.0000
   2.000   0.6243   0.01483   0.00599  -0.0798   0.6386   1.0000
   2.250   0.6496   0.01498   0.00605  -0.0792   0.6269   1.0000
   2.500   0.6752   0.01513   0.00610  -0.0787   0.6156   1.0000
   2.750   0.7006   0.01530   0.00620  -0.0781   0.6040   1.0000
   3.000   0.7255   0.01549   0.00636  -0.0775   0.5922   1.0000
   3.250   0.7507   0.01569   0.00651  -0.0769   0.5811   1.0000
   3.500   0.7763   0.01588   0.00663  -0.0764   0.5704   1.0000
   3.750   0.8008   0.01609   0.00685  -0.0758   0.5582   1.0000
   4.000   0.8256   0.01631   0.00707  -0.0752   0.5463   1.0000
   4.250   0.8503   0.01653   0.00727  -0.0746   0.5342   1.0000
   4.500   0.8749   0.01675   0.00747  -0.0740   0.5219   1.0000
   4.750   0.8990   0.01698   0.00772  -0.0733   0.5083   1.0000
   5.000   0.9226   0.01723   0.00798  -0.0725   0.4934   1.0000
   5.250   0.9459   0.01748   0.00824  -0.0717   0.4772   1.0000
   5.500   0.9686   0.01776   0.00853  -0.0708   0.4596   1.0000
   5.750   0.9909   0.01806   0.00885  -0.0699   0.4401   1.0000
   6.000   1.0128   0.01840   0.00916  -0.0688   0.4197   1.0000
   6.250   1.0338   0.01880   0.00950  -0.0677   0.3988   1.0000
   6.500   1.0542   0.01925   0.00991  -0.0665   0.3772   1.0000
   6.750   1.0736   0.01978   0.01035  -0.0653   0.3572   1.0000
   7.000   1.0926   0.02037   0.01086  -0.0639   0.3396   1.0000
   7.250   1.1115   0.02099   0.01144  -0.0627   0.3242   1.0000
   7.500   1.1307   0.02162   0.01206  -0.0614   0.3110   1.0000
   7.750   1.1502   0.02225   0.01271  -0.0603   0.2999   1.0000
   8.000   1.1692   0.02292   0.01337  -0.0591   0.2906   1.0000
   8.250   1.1887   0.02358   0.01408  -0.0580   0.2819   1.0000
   8.500   1.2079   0.02427   0.01481  -0.0569   0.2743   1.0000
   8.750   1.2272   0.02496   0.01556  -0.0558   0.2669   1.0000
   9.000   1.2465   0.02569   0.01631  -0.0547   0.2608   1.0000
   9.250   1.2656   0.02638   0.01714  -0.0536   0.2541   1.0000
   9.500   1.2835   0.02714   0.01792  -0.0524   0.2477   1.0000
   9.750   1.3002   0.02787   0.01880  -0.0511   0.2404   1.0000
  10.000   1.3146   0.02863   0.01960  -0.0494   0.2336   1.0000
  10.250   1.3268   0.02940   0.02052  -0.0474   0.2257   1.0000
  10.500   1.3352   0.03027   0.02139  -0.0451   0.2166   1.0000
  10.750   1.3410   0.03121   0.02251  -0.0427   0.2056   1.0000
  11.000   1.3465   0.03229   0.02370  -0.0406   0.1943   1.0000
  11.250   1.3520   0.03351   0.02499  -0.0386   0.1842   1.0000
  11.500   1.3574   0.03484   0.02643  -0.0369   0.1743   1.0000
  11.750   1.3629   0.03629   0.02803  -0.0354   0.1626   1.0000
  12.000   1.3669   0.03795   0.02982  -0.0340   0.1496   1.0000
  12.250   1.3692   0.03987   0.03184  -0.0328   0.1335   1.0000
  12.500   1.3679   0.04225   0.03426  -0.0316   0.1076   1.0000
  12.750   1.3562   0.04575   0.03755  -0.0305   0.0792   1.0000
  13.000   1.3426   0.04974   0.04141  -0.0297   0.0654   1.0000
  13.250   1.3305   0.05382   0.04550  -0.0292   0.0578   1.0000
  13.500   1.3181   0.05816   0.04991  -0.0291   0.0527   1.0000
  13.750   1.3052   0.06274   0.05461  -0.0294   0.0492   1.0000
  14.000   1.2937   0.06739   0.05943  -0.0300   0.0459   1.0000
  14.250   1.2797   0.07258   0.06477  -0.0310   0.0437   1.0000
  14.500   1.2633   0.07836   0.07067  -0.0325   0.0421   1.0000
  14.750   1.2478   0.08426   0.07670  -0.0342   0.0408   1.0000
  15.000   1.2345   0.08999   0.08262  -0.0360   0.0392   1.0000
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