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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 50,000
Max Cl/Cd: 37.84 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m19-il-50000-n5.txt
Download as CSV file: xf-m19-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M19 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3537   0.11938   0.11360  -0.0032   1.0000   0.0451
  -8.500  -0.3480   0.11782   0.11213  -0.0067   1.0000   0.0457
  -8.250  -0.3429   0.11642   0.11084  -0.0107   1.0000   0.0460
  -8.000  -0.3347   0.11490   0.10940  -0.0158   1.0000   0.0462
  -7.750  -0.3230   0.10829   0.10289  -0.0153   1.0000   0.0470
  -7.500  -0.3110   0.10236   0.09699  -0.0141   1.0000   0.0495
  -7.250  -0.3002   0.09908   0.09378  -0.0167   1.0000   0.0523
  -7.000  -0.2890   0.09639   0.09112  -0.0204   1.0000   0.0556
  -6.750  -0.2620   0.09508   0.08974  -0.0312   0.9497   0.0588
  -6.250  -0.2256   0.08565   0.08022  -0.0367   0.9105   0.0622
  -6.000  -0.2094   0.08218   0.07666  -0.0386   0.8940   0.0656
  -5.750  -0.1900   0.07959   0.07395  -0.0423   0.8783   0.0701
  -5.500  -0.1555   0.07990   0.07395  -0.0515   0.8626   0.0730
  -5.250  -0.1529   0.07362   0.06777  -0.0478   0.8522   0.0758
  -5.000  -0.1354   0.07075   0.06479  -0.0492   0.8404   0.0830
  -4.750  -0.1064   0.06888   0.06270  -0.0544   0.8287   0.0879
  -4.500  -0.0941   0.06485   0.05860  -0.0535   0.8187   0.0921
  -4.250  -0.0571   0.06446   0.05779  -0.0591   0.8084   0.1007
  -4.000  -0.0462   0.05955   0.05294  -0.0580   0.7993   0.1040
  -3.750  -0.0182   0.05765   0.05078  -0.0607   0.7896   0.1163
  -3.500   0.0104   0.05631   0.04909  -0.0627   0.7811   0.1293
  -3.250   0.0246   0.05183   0.04469  -0.0620   0.7721   0.1340
  -3.000   0.0518   0.04976   0.04233  -0.0636   0.7637   0.1458
  -2.500   0.0979   0.04525   0.03748  -0.0648   0.7468   0.1886
  -2.250   0.1192   0.04297   0.03503  -0.0647   0.7397   0.2181
  -2.000   0.1412   0.04078   0.03273  -0.0648   0.7308   0.2516
  -1.500   0.2290   0.03773   0.02835  -0.0683   0.7156   0.0952
  -1.250   0.2601   0.03617   0.02629  -0.0683   0.7092   0.0845
  -1.000   0.2879   0.03478   0.02465  -0.0686   0.7006   0.0828
  -0.750   0.3171   0.03383   0.02326  -0.0684   0.6940   0.0877
  -0.500   0.3458   0.03289   0.02195  -0.0684   0.6858   0.0871
  -0.250   0.3729   0.03169   0.02051  -0.0682   0.6792   0.0853
   0.000   0.4011   0.03077   0.01937  -0.0684   0.6712   0.0837
   0.250   0.4289   0.02994   0.01826  -0.0681   0.6648   0.0822
   0.500   0.4574   0.02932   0.01736  -0.0681   0.6569   0.0811
   0.750   0.4883   0.02870   0.01640  -0.0681   0.6506   0.0802
   1.000   0.5188   0.02829   0.01574  -0.0685   0.6427   0.0798
   1.250   0.5478   0.02779   0.01501  -0.0682   0.6369   0.0799
   1.500   0.5750   0.02759   0.01469  -0.0682   0.6287   0.0806
   1.750   0.6009   0.02722   0.01414  -0.0673   0.6236   0.0819
   2.000   0.6257   0.02729   0.01415  -0.0672   0.6152   0.0840
   2.250   0.6506   0.02710   0.01382  -0.0663   0.6099   0.0871
   2.500   0.6748   0.02730   0.01408  -0.0663   0.6020   0.0926
   2.750   0.6996   0.02728   0.01401  -0.0656   0.5965   0.1033
   3.000   0.7235   0.02747   0.01442  -0.0654   0.5894   0.1464
   3.250   0.7634   0.02634   0.01452  -0.0681   0.5831   1.0000
   3.500   0.7875   0.02688   0.01497  -0.0677   0.5769   1.0000
   3.750   0.8112   0.02749   0.01554  -0.0674   0.5702   1.0000
   4.000   0.8362   0.02775   0.01572  -0.0666   0.5659   1.0000
   4.250   0.8580   0.02876   0.01688  -0.0667   0.5577   1.0000
   4.500   0.8825   0.02917   0.01730  -0.0661   0.5530   1.0000
   4.750   0.9041   0.03014   0.01840  -0.0660   0.5461   1.0000
   5.000   0.9273   0.03079   0.01915  -0.0656   0.5405   1.0000
   5.250   0.9517   0.03124   0.01974  -0.0650   0.5363   1.0000
   5.500   0.9703   0.03267   0.02142  -0.0651   0.5286   1.0000
   5.750   0.9944   0.03319   0.02210  -0.0644   0.5243   1.0000
   6.000   1.0125   0.03459   0.02375  -0.0643   0.5172   1.0000
   6.250   1.0429   0.03177   0.02092  -0.0607   0.4953   1.0000
   6.500   1.0667   0.03122   0.02060  -0.0590   0.4804   1.0000
   6.750   1.0860   0.02972   0.01917  -0.0560   0.4430   1.0000
   7.000   1.1050   0.02947   0.01909  -0.0541   0.4137   1.0000
   7.250   1.1185   0.02956   0.01915  -0.0519   0.3564   1.0000
   7.500   1.1192   0.03115   0.01977  -0.0491   0.1991   1.0000
   7.750   1.0968   0.03594   0.02346  -0.0469   0.0771   1.0000
   8.000   1.0872   0.03940   0.02675  -0.0453   0.0519   1.0000
   8.250   1.0838   0.04239   0.02983  -0.0444   0.0466   1.0000
   8.500   1.0809   0.04552   0.03317  -0.0438   0.0435   1.0000
   8.750   1.0767   0.04893   0.03671  -0.0434   0.0412   1.0000
   9.000   1.0731   0.05237   0.04029  -0.0431   0.0394   1.0000
   9.250   1.0702   0.05577   0.04388  -0.0429   0.0375   1.0000
   9.500   1.0664   0.05931   0.04758  -0.0428   0.0357   1.0000
   9.750   1.0620   0.06295   0.05135  -0.0427   0.0343   1.0000
  10.000   1.0569   0.06668   0.05518  -0.0427   0.0331   1.0000
  10.250   1.0518   0.07037   0.05898  -0.0425   0.0323   1.0000
  10.500   1.0512   0.07346   0.06220  -0.0420   0.0318   1.0000
  10.750   1.0525   0.07623   0.06511  -0.0413   0.0313   1.0000
  11.000   1.0564   0.07855   0.06758  -0.0402   0.0308   1.0000
  11.250   1.0644   0.08020   0.06938  -0.0384   0.0302   1.0000
  11.500   1.0787   0.08099   0.07033  -0.0358   0.0293   1.0000
  11.750   1.1010   0.08095   0.07056  -0.0322   0.0275   1.0000
  12.000   1.1475   0.07901   0.06880  -0.0262   0.0255   1.0000
  12.250   1.1902   0.07958   0.06969  -0.0219   0.0253   1.0000
  12.500   1.2042   0.08266   0.07312  -0.0206   0.0254   1.0000
  12.750   1.2054   0.08656   0.07737  -0.0203   0.0256   1.0000
  13.000   1.2013   0.09087   0.08201  -0.0206   0.0258   1.0000
  13.250   1.1935   0.09554   0.08698  -0.0214   0.0261   1.0000
  13.500   1.1830   0.10057   0.09230  -0.0227   0.0263   1.0000
  13.750   1.1705   0.10594   0.09793  -0.0245   0.0265   1.0000
  14.000   1.1564   0.11167   0.10390  -0.0269   0.0268   1.0000
  14.250   1.1415   0.11780   0.11026  -0.0298   0.0270   1.0000
  14.500   1.1263   0.12440   0.11705  -0.0334   0.0273   1.0000
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