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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 50,000
Max Cl/Cd: 26.58 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe426-il-50000-n5.txt
Download as CSV file: xf-goe426-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2596   0.11000   0.10329  -0.0410   1.0000   0.1531
  -9.000  -0.2842   0.10981   0.10330  -0.0409   1.0000   0.1579
  -8.750  -0.3152   0.11001   0.10372  -0.0396   1.0000   0.1588
  -8.500  -0.3169   0.10736   0.10119  -0.0371   1.0000   0.1597
  -8.250  -0.3008   0.10370   0.09754  -0.0364   0.9969   0.1617
  -7.750  -0.2826   0.08854   0.08220  -0.0558   0.9678   0.0926
  -7.500  -0.2852   0.07831   0.07184  -0.0721   0.9481   0.0819
  -7.250  -0.2662   0.07386   0.06729  -0.0765   0.9366   0.0809
  -7.000  -0.2482   0.06890   0.06219  -0.0823   0.9255   0.0805
  -6.750  -0.2313   0.06422   0.05733  -0.0872   0.9137   0.0800
  -6.500  -0.2173   0.06014   0.05306  -0.0905   0.9002   0.0793
  -6.250  -0.2015   0.05625   0.04893  -0.0933   0.8876   0.0782
  -6.000  -0.1818   0.05224   0.04457  -0.0964   0.8771   0.0771
  -5.750  -0.1630   0.04874   0.04070  -0.0983   0.8654   0.0763
  -5.500  -0.1443   0.04574   0.03729  -0.0993   0.8533   0.0757
  -5.250  -0.1200   0.04288   0.03399  -0.1007   0.8436   0.0754
  -5.000  -0.0956   0.04062   0.03133  -0.1014   0.8333   0.0762
  -4.750  -0.0724   0.03877   0.02908  -0.1015   0.8224   0.0777
  -4.500  -0.0421   0.03678   0.02664  -0.1024   0.8148   0.0791
  -4.250  -0.0190   0.03531   0.02481  -0.1020   0.8035   0.0798
  -4.000   0.0096   0.03381   0.02293  -0.1021   0.7951   0.0803
  -3.750   0.0367   0.03257   0.02138  -0.1019   0.7858   0.0810
  -3.500   0.0642   0.03147   0.02005  -0.1017   0.7770   0.0820
  -3.250   0.0921   0.03045   0.01895  -0.1016   0.7688   0.0840
  -3.000   0.1179   0.02976   0.01818  -0.1012   0.7599   0.0873
  -2.750   0.1462   0.02906   0.01732  -0.1009   0.7521   0.0913
  -2.500   0.1720   0.02855   0.01660  -0.1002   0.7437   0.0943
  -2.250   0.1990   0.02789   0.01591  -0.0999   0.7361   0.0975
  -2.000   0.2248   0.02744   0.01537  -0.0995   0.7283   0.1019
  -1.750   0.2504   0.02713   0.01489  -0.0990   0.7203   0.1094
  -1.500   0.2782   0.02660   0.01434  -0.0990   0.7140   0.1213
  -1.250   0.3010   0.02631   0.01409  -0.0985   0.7054   0.1382
  -1.000   0.3282   0.02476   0.01361  -0.0991   0.6999   0.3224
  -0.750   0.3382   0.02422   0.01421  -0.0953   0.6916   0.6272
  -0.500   0.3531   0.02388   0.01431  -0.0909   0.6855   0.7907
  -0.250   0.4133   0.02351   0.01392  -0.0957   0.6793   1.0000
   0.000   0.4343   0.02391   0.01406  -0.0951   0.6713   1.0000
   0.250   0.4633   0.02405   0.01388  -0.0953   0.6662   1.0000
   0.500   0.4817   0.02465   0.01431  -0.0945   0.6577   1.0000
   0.750   0.5089   0.02489   0.01431  -0.0944   0.6518   1.0000
   1.000   0.5319   0.02535   0.01460  -0.0940   0.6451   1.0000
   1.250   0.5547   0.02581   0.01491  -0.0935   0.6381   1.0000
   1.500   0.5848   0.02594   0.01484  -0.0937   0.6333   1.0000
   1.750   0.6014   0.02675   0.01558  -0.0926   0.6250   1.0000
   2.000   0.6285   0.02703   0.01572  -0.0924   0.6195   1.0000
   2.250   0.6514   0.02754   0.01613  -0.0919   0.6132   1.0000
   2.500   0.6720   0.02818   0.01671  -0.0912   0.6062   1.0000
   2.750   0.7020   0.02834   0.01674  -0.0913   0.6017   1.0000
   3.000   0.7169   0.02929   0.01769  -0.0900   0.5937   1.0000
   3.250   0.7423   0.02970   0.01803  -0.0897   0.5881   1.0000
   3.500   0.7712   0.02995   0.01819  -0.0897   0.5836   1.0000
   3.750   0.7826   0.03113   0.01942  -0.0881   0.5751   1.0000
   4.000   0.8114   0.03137   0.01960  -0.0881   0.5705   1.0000
   4.250   0.8264   0.03241   0.02067  -0.0869   0.5634   1.0000
   4.500   0.8463   0.03315   0.02142  -0.0861   0.5570   1.0000
   4.750   0.8781   0.03325   0.02148  -0.0863   0.5531   1.0000
   5.000   0.8816   0.03498   0.02330  -0.0841   0.5442   1.0000
   5.250   0.9070   0.03544   0.02376  -0.0838   0.5392   1.0000
   5.500   0.9413   0.03542   0.02373  -0.0842   0.5359   1.0000
   5.750   0.9328   0.03789   0.02633  -0.0811   0.5255   1.0000
   6.000   0.9625   0.03812   0.02658  -0.0811   0.5214   1.0000
   6.500   0.9770   0.04131   0.02993  -0.0776   0.5069   1.0000
   6.750   1.0114   0.04127   0.02993  -0.0779   0.5037   1.0000
   7.000   0.9793   0.04532   0.03407  -0.0734   0.4919   1.0000
   7.250   1.0106   0.04541   0.03423  -0.0734   0.4883   1.0000
   7.750   1.0022   0.05065   0.03960  -0.0695   0.4724   1.0000
   8.000   1.0378   0.05031   0.03936  -0.0695   0.4700   1.0000
   8.500   0.9675   0.06270   0.05187  -0.0668   0.4435   1.0000
   8.750   0.9922   0.06310   0.05236  -0.0662   0.4402   1.0000
   9.250   0.9906   0.06949   0.05891  -0.0654   0.4248   1.0000
   9.750   0.9911   0.07576   0.06536  -0.0649   0.4100   1.0000
  10.000   1.0203   0.07563   0.06538  -0.0641   0.4073   1.0000
  10.250   0.9943   0.08182   0.07163  -0.0646   0.3955   1.0000
  10.500   1.0230   0.08165   0.07161  -0.0637   0.3924   1.0000
  10.750   1.0029   0.08718   0.07721  -0.0642   0.3809   1.0000
  11.000   1.0359   0.08618   0.07637  -0.0630   0.3771   1.0000
  11.250   1.0214   0.09089   0.08116  -0.0633   0.3650   1.0000
  11.500   1.0593   0.08888   0.07935  -0.0617   0.3612   1.0000
  11.750   1.0442   0.09379   0.08434  -0.0622   0.3488   1.0000
  12.000   1.0389   0.09760   0.08826  -0.0625   0.3384   1.0000
  12.250   1.0643   0.09716   0.08800  -0.0614   0.3328   1.0000
  12.750   1.0847   0.10039   0.09157  -0.0605   0.3165   1.0000
  13.000   1.0736   0.10514   0.09641  -0.0614   0.3040   1.0000
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