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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 500,000
Max Cl/Cd: 102.93 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m14-il-500000.txt
Download as CSV file: xf-m14-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M14 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4524   0.11936   0.11710  -0.0022   1.0000   0.0190
  -9.750  -0.4505   0.11581   0.11356  -0.0052   1.0000   0.0191
  -9.500  -0.4472   0.11203   0.10980  -0.0077   1.0000   0.0192
  -9.250  -0.4431   0.10816   0.10595  -0.0101   1.0000   0.0192
  -9.000  -0.4387   0.10430   0.10210  -0.0124   1.0000   0.0192
  -8.750  -0.4385   0.09910   0.09693  -0.0135   1.0000   0.0195
  -8.500  -0.4298   0.09597   0.09380  -0.0127   1.0000   0.0198
  -8.250  -0.4227   0.09301   0.09085  -0.0134   1.0000   0.0201
  -8.000  -0.4169   0.09000   0.08786  -0.0147   1.0000   0.0204
  -7.750  -0.4121   0.08697   0.08485  -0.0164   1.0000   0.0208
  -7.500  -0.4073   0.08380   0.08171  -0.0189   1.0000   0.0215
  -7.250  -0.3985   0.08010   0.07802  -0.0227   1.0000   0.0225
  -7.000  -0.3836   0.07531   0.07320  -0.0309   1.0000   0.0243
  -6.750  -0.3672   0.07066   0.06850  -0.0369   1.0000   0.0247
  -6.500  -0.3555   0.06670   0.06450  -0.0393   0.9998   0.0248
  -6.250  -0.3240   0.06078   0.05845  -0.0464   0.9903   0.0248
  -6.000  -0.3080   0.05405   0.05166  -0.0507   0.9779   0.0257
  -5.750  -0.2831   0.05162   0.04917  -0.0530   0.9629   0.0265
  -5.500  -0.2587   0.04873   0.04618  -0.0552   0.9432   0.0276
  -4.750  -0.1864   0.03520   0.03168  -0.0590   0.8824   0.0329
  -4.500  -0.1688   0.03290   0.02927  -0.0589   0.8647   0.0339
  -4.250  -0.1473   0.03148   0.02772  -0.0587   0.8479   0.0349
  -4.000  -0.1240   0.02972   0.02578  -0.0586   0.8325   0.0364
  -3.750  -0.0988   0.02758   0.02337  -0.0585   0.8183   0.0391
  -3.500  -0.0677   0.02726   0.02258  -0.0576   0.8049   0.0422
  -3.000  -0.0230   0.02163   0.01660  -0.0579   0.7800   0.0469
  -2.750   0.0045   0.02081   0.01553  -0.0576   0.7681   0.0519
  -2.500   0.0302   0.01882   0.01323  -0.0575   0.7570   0.0568
  -2.250   0.0565   0.01805   0.01238  -0.0574   0.7461   0.0596
  -2.000   0.0862   0.01944   0.01354  -0.0569   0.7346   0.0667
  -1.750   0.1108   0.01631   0.01028  -0.0572   0.7242   0.0716
  -1.500   0.1423   0.01314   0.00634  -0.0557   0.7154   0.0433
  -1.250   0.1702   0.01264   0.00575  -0.0555   0.7052   0.0416
  -1.000   0.1979   0.01170   0.00470  -0.0553   0.6952   0.0410
  -0.750   0.2254   0.01115   0.00406  -0.0551   0.6859   0.0410
  -0.500   0.2529   0.01073   0.00357  -0.0549   0.6764   0.0412
  -0.250   0.2806   0.01038   0.00319  -0.0548   0.6670   0.0415
   0.000   0.3081   0.01011   0.00286  -0.0547   0.6582   0.0417
   0.250   0.3358   0.00989   0.00261  -0.0546   0.6487   0.0424
   0.500   0.3633   0.00960   0.00228  -0.0545   0.6399   0.0436
   0.750   0.3910   0.00945   0.00207  -0.0545   0.6313   0.0446
   1.000   0.4191   0.00932   0.00194  -0.0545   0.6220   0.0467
   1.250   0.4470   0.00927   0.00185  -0.0544   0.6134   0.0504
   1.500   0.4750   0.00920   0.00180  -0.0544   0.6045   0.0642
   1.750   0.4992   0.00799   0.00189  -0.0545   0.5963   0.5724
   2.250   0.5707   0.00712   0.00198  -0.0576   0.5779   1.0000
   2.500   0.5972   0.00723   0.00202  -0.0573   0.5698   1.0000
   2.750   0.6238   0.00732   0.00207  -0.0571   0.5607   1.0000
   3.000   0.6506   0.00742   0.00214  -0.0569   0.5518   1.0000
   3.250   0.6771   0.00755   0.00220  -0.0566   0.5434   1.0000
   3.500   0.7041   0.00763   0.00230  -0.0565   0.5342   1.0000
   3.750   0.7309   0.00776   0.00240  -0.0563   0.5254   1.0000
   4.000   0.7577   0.00789   0.00250  -0.0562   0.5159   1.0000
   4.250   0.7847   0.00801   0.00264  -0.0560   0.5066   1.0000
   4.500   0.8114   0.00815   0.00276  -0.0559   0.4953   1.0000
   4.750   0.8379   0.00828   0.00287  -0.0557   0.4781   1.0000
   5.000   0.8639   0.00847   0.00297  -0.0554   0.4562   1.0000
   5.250   0.8903   0.00865   0.00313  -0.0552   0.4363   1.0000
   5.500   0.9160   0.00890   0.00329  -0.0550   0.4102   1.0000
   5.750   0.9416   0.00918   0.00349  -0.0547   0.3844   1.0000
   6.000   0.9672   0.00948   0.00373  -0.0545   0.3591   1.0000
   6.250   0.9917   0.00991   0.00404  -0.0541   0.3247   1.0000
   6.500   1.0137   0.01067   0.00448  -0.0535   0.2573   1.0000
   6.750   1.0246   0.01292   0.00575  -0.0517   0.0877   1.0000
   7.000   1.0416   0.01433   0.00683  -0.0504   0.0314   1.0000
   7.250   1.0628   0.01516   0.00769  -0.0494   0.0254   1.0000
   7.500   1.0859   0.01568   0.00827  -0.0488   0.0232   1.0000
   7.750   1.1076   0.01633   0.00896  -0.0480   0.0212   1.0000
   8.000   1.1258   0.01735   0.01005  -0.0467   0.0195   1.0000
   8.250   1.1424   0.01847   0.01128  -0.0452   0.0186   1.0000
   8.500   1.1610   0.01930   0.01221  -0.0439   0.0179   1.0000
   8.750   1.1783   0.02021   0.01320  -0.0426   0.0171   1.0000
   9.000   1.1952   0.02110   0.01415  -0.0412   0.0162   1.0000
   9.250   1.2109   0.02205   0.01514  -0.0397   0.0154   1.0000
   9.500   1.2225   0.02331   0.01645  -0.0377   0.0148   1.0000
   9.750   1.2287   0.02512   0.01834  -0.0350   0.0142   1.0000
  10.000   1.2347   0.02735   0.02066  -0.0322   0.0139   1.0000
  10.250   1.2474   0.02839   0.02181  -0.0302   0.0137   1.0000
  10.500   1.2598   0.02969   0.02323  -0.0284   0.0134   1.0000
  10.750   1.2721   0.03120   0.02486  -0.0267   0.0131   1.0000
  11.000   1.2845   0.03294   0.02675  -0.0250   0.0129   1.0000
  11.250   1.2959   0.03483   0.02880  -0.0234   0.0126   1.0000
  11.500   1.3050   0.03671   0.03084  -0.0217   0.0123   1.0000
  11.750   1.3121   0.03858   0.03288  -0.0200   0.0119   1.0000
  12.000   1.3177   0.04049   0.03492  -0.0184   0.0116   1.0000
  12.250   1.3217   0.04270   0.03729  -0.0170   0.0114   1.0000
  12.500   1.3223   0.04554   0.04034  -0.0154   0.0113   1.0000
  12.750   1.3178   0.04903   0.04409  -0.0139   0.0114   1.0000
  13.000   1.3061   0.05362   0.04901  -0.0124   0.0116   1.0000
  13.250   1.2889   0.05884   0.05455  -0.0115   0.0119   1.0000
  13.500   1.2694   0.06435   0.06034  -0.0114   0.0122   1.0000
  13.750   1.2496   0.06999   0.06621  -0.0121   0.0125   1.0000
  14.000   1.2296   0.07583   0.07226  -0.0135   0.0127   1.0000
  14.250   1.2088   0.08208   0.07869  -0.0156   0.0129   1.0000
  14.500   1.1874   0.08871   0.08548  -0.0183   0.0131   1.0000
  14.750   1.1652   0.09591   0.09283  -0.0215   0.0133   1.0000
  15.000   1.0112   0.09304   0.09005  -0.0079   0.0128   1.0000
  15.250   0.9844   0.09952   0.09667  -0.0106   0.0129   1.0000
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