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GOE 648 AIRFOIL (goe648-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 648 AIRFOIL (goe648-il)
Reynolds number: 50,000
Max Cl/Cd: 30.47 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe648-il-50000-n5.txt
Download as CSV file: xf-goe648-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 648 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3456   0.10086   0.09353  -0.0452   1.0000   0.0852
 -10.000  -0.3575   0.09680   0.08956  -0.0458   1.0000   0.0857
  -9.750  -0.3736   0.09243   0.08530  -0.0465   1.0000   0.0860
  -9.500  -0.3940   0.08779   0.08077  -0.0471   1.0000   0.0861
  -9.250  -0.4205   0.08275   0.07584  -0.0479   1.0000   0.0858
  -9.000  -0.4616   0.07694   0.07013  -0.0489   1.0000   0.0851
  -8.750  -0.5071   0.07249   0.06573  -0.0475   1.0000   0.0843
  -8.500  -0.5444   0.06781   0.06097  -0.0460   1.0000   0.0839
  -8.250  -0.5714   0.06351   0.05652  -0.0444   1.0000   0.0840
  -8.000  -0.5898   0.05949   0.05228  -0.0427   1.0000   0.0845
  -7.750  -0.5919   0.05479   0.04715  -0.0437   0.9960   0.0859
  -7.500  -0.5809   0.04926   0.04078  -0.0468   0.9869   0.0887
  -7.250  -0.5527   0.04736   0.03883  -0.0487   0.9801   0.0913
  -7.000  -0.5275   0.04515   0.03637  -0.0501   0.9722   0.0940
  -6.750  -0.5031   0.04262   0.03337  -0.0515   0.9644   0.0978
  -6.500  -0.4754   0.04045   0.03081  -0.0529   0.9569   0.1017
  -6.250  -0.4482   0.03913   0.02941  -0.0536   0.9488   0.1053
  -6.000  -0.4171   0.03754   0.02746  -0.0550   0.9416   0.1106
  -5.750  -0.3907   0.03629   0.02605  -0.0553   0.9331   0.1152
  -5.500  -0.3578   0.03527   0.02491  -0.0567   0.9258   0.1213
  -5.250  -0.3308   0.03421   0.02362  -0.0568   0.9170   0.1277
  -5.000  -0.2980   0.03342   0.02284  -0.0580   0.9096   0.1352
  -4.750  -0.2700   0.03260   0.02187  -0.0582   0.9007   0.1430
  -4.500  -0.2375   0.03192   0.02116  -0.0592   0.8930   0.1529
  -4.250  -0.2090   0.03127   0.02052  -0.0594   0.8841   0.1627
  -4.000  -0.1766   0.03063   0.01981  -0.0601   0.8759   0.1753
  -3.750  -0.1464   0.03009   0.01923  -0.0605   0.8674   0.1899
  -3.500  -0.1149   0.02951   0.01872  -0.0612   0.8585   0.2077
  -3.250  -0.0830   0.02889   0.01823  -0.0619   0.8493   0.2308
  -3.000  -0.0478   0.02813   0.01761  -0.0629   0.8393   0.2658
  -2.750  -0.0185   0.02741   0.01706  -0.0628   0.8263   0.3090
  -2.500   0.0262   0.02634   0.01628  -0.0649   0.8173   0.3776
  -2.250   0.0511   0.02577   0.01598  -0.0636   0.8025   0.4404
  -2.000   0.0758   0.02533   0.01578  -0.0621   0.7888   0.5111
  -1.750   0.1108   0.02472   0.01543  -0.0618   0.7805   0.5970
  -1.500   0.1286   0.02454   0.01547  -0.0588   0.7666   0.6619
  -1.250   0.1523   0.02431   0.01541  -0.0566   0.7544   0.7272
  -1.000   0.1891   0.02388   0.01501  -0.0564   0.7450   0.7921
  -0.750   0.2279   0.02370   0.01487  -0.0571   0.7308   0.8515
  -0.500   0.2947   0.02346   0.01454  -0.0631   0.7171   0.9088
  -0.250   0.3664   0.02319   0.01406  -0.0705   0.7022   0.9536
   0.000   0.4307   0.02293   0.01356  -0.0770   0.6854   0.9934
   0.250   0.4545   0.02278   0.01320  -0.0764   0.6693   1.0000
   0.500   0.4742   0.02268   0.01287  -0.0749   0.6532   1.0000
   0.750   0.4950   0.02265   0.01262  -0.0734   0.6364   1.0000
   1.000   0.5150   0.02270   0.01247  -0.0718   0.6188   1.0000
   1.250   0.5358   0.02280   0.01236  -0.0703   0.6009   1.0000
   1.500   0.5567   0.02296   0.01232  -0.0688   0.5831   1.0000
   1.750   0.5776   0.02317   0.01235  -0.0674   0.5654   1.0000
   2.000   0.5985   0.02343   0.01242  -0.0660   0.5479   1.0000
   2.250   0.6194   0.02373   0.01255  -0.0646   0.5312   1.0000
   2.500   0.6405   0.02407   0.01273  -0.0633   0.5154   1.0000
   2.750   0.6626   0.02444   0.01293  -0.0622   0.5010   1.0000
   3.000   0.6863   0.02479   0.01310  -0.0613   0.4880   1.0000
   3.250   0.7076   0.02523   0.01342  -0.0602   0.4751   1.0000
   3.500   0.7285   0.02570   0.01379  -0.0590   0.4630   1.0000
   3.750   0.7532   0.02611   0.01403  -0.0584   0.4529   1.0000
   4.000   0.7737   0.02665   0.01453  -0.0572   0.4423   1.0000
   4.250   0.7971   0.02714   0.01490  -0.0565   0.4332   1.0000
   4.500   0.8185   0.02768   0.01538  -0.0555   0.4239   1.0000
   4.750   0.8417   0.02822   0.01584  -0.0548   0.4158   1.0000
   5.000   0.8625   0.02883   0.01642  -0.0537   0.4075   1.0000
   5.250   0.8874   0.02935   0.01682  -0.0533   0.4003   1.0000
   5.500   0.9052   0.03008   0.01759  -0.0519   0.3923   1.0000
   5.750   0.9313   0.03060   0.01800  -0.0516   0.3858   1.0000
   6.000   0.9486   0.03141   0.01886  -0.0502   0.3787   1.0000
   6.250   0.9692   0.03210   0.01955  -0.0492   0.3719   1.0000
   6.500   0.9960   0.03269   0.02002  -0.0491   0.3661   1.0000
   6.750   1.0084   0.03370   0.02117  -0.0472   0.3595   1.0000
   7.000   1.0293   0.03444   0.02192  -0.0463   0.3535   1.0000
   7.250   1.0553   0.03512   0.02250  -0.0461   0.3480   1.0000
   7.500   1.0635   0.03631   0.02388  -0.0437   0.3419   1.0000
   7.750   1.0815   0.03722   0.02483  -0.0426   0.3363   1.0000
   8.000   1.1115   0.03782   0.02533  -0.0430   0.3314   1.0000
   8.250   1.1132   0.03930   0.02701  -0.0399   0.3260   1.0000
   8.500   1.1224   0.04055   0.02838  -0.0378   0.3206   1.0000
   8.750   1.1443   0.04140   0.02923  -0.0372   0.3158   1.0000
   9.000   1.1635   0.04244   0.03029  -0.0364   0.3114   1.0000
   9.250   1.1503   0.04441   0.03250  -0.0318   0.3065   1.0000
   9.500   1.1518   0.04602   0.03423  -0.0292   0.3018   1.0000
   9.750   1.1728   0.04693   0.03515  -0.0286   0.2975   1.0000
  10.000   1.1904   0.04810   0.03634  -0.0277   0.2937   1.0000
  10.250   1.1490   0.05193   0.04048  -0.0221   0.2894   1.0000
  10.500   1.1172   0.05605   0.04480  -0.0187   0.2848   1.0000
  10.750   1.1204   0.05810   0.04693  -0.0175   0.2808   1.0000
  11.000   1.1700   0.05705   0.04580  -0.0181   0.2774   1.0000
  11.250   0.9302   0.08542   0.07465  -0.0206   0.2631   1.0000
  11.500   0.9520   0.08574   0.07500  -0.0197   0.2609   1.0000
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