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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 100,000
Max Cl/Cd: 57.42 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m19-il-100000-n5.txt
Download as CSV file: xf-m19-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3544   0.11707   0.11309  -0.0052   0.9296   0.0245
  -8.250  -0.3474   0.11431   0.11026  -0.0074   0.8893   0.0245
  -8.000  -0.3419   0.11170   0.10759  -0.0091   0.8664   0.0245
  -7.750  -0.2372   0.08950   0.08537  -0.0145   0.8080   0.0257
  -7.500  -0.2320   0.08582   0.08164  -0.0145   0.7988   0.0264
  -6.750  -0.2964   0.09172   0.08738  -0.0144   0.8033   0.0257
  -6.500  -0.2858   0.08812   0.08369  -0.0153   0.7939   0.0264
  -6.250  -0.2725   0.08478   0.08031  -0.0175   0.7845   0.0270
  -6.000  -0.2571   0.08149   0.07696  -0.0201   0.7754   0.0279
  -5.750  -0.2404   0.07827   0.07365  -0.0228   0.7676   0.0290
  -5.500  -0.2207   0.07501   0.07032  -0.0261   0.7586   0.0305
  -5.250  -0.1958   0.07212   0.06730  -0.0304   0.7510   0.0330
  -5.000  -0.1524   0.07094   0.06584  -0.0391   0.7425   0.0346
  -4.750  -0.1325   0.06649   0.06130  -0.0412   0.7356   0.0352
  -4.500  -0.1244   0.06181   0.05664  -0.0400   0.7283   0.0366
  -4.250  -0.1042   0.05863   0.05334  -0.0413   0.7215   0.0387
  -4.000  -0.0775   0.05577   0.05031  -0.0437   0.7140   0.0423
  -3.750  -0.0374   0.05341   0.04762  -0.0484   0.7075   0.0472
  -3.500  -0.0236   0.04997   0.04418  -0.0480   0.7003   0.0513
  -3.250   0.0236   0.04981   0.04346  -0.0519   0.6939   0.0592
  -3.000   0.0412   0.04514   0.03880  -0.0524   0.6869   0.0608
  -2.750   0.0604   0.04257   0.03610  -0.0524   0.6812   0.0682
  -2.500   0.0952   0.04060   0.03380  -0.0543   0.6738   0.0747
  -2.250   0.1180   0.03807   0.03114  -0.0545   0.6678   0.0781
  -2.000   0.1583   0.03828   0.03075  -0.0557   0.6607   0.0870
  -1.750   0.1748   0.03435   0.02694  -0.0559   0.6547   0.0920
  -1.500   0.2067   0.03321   0.02541  -0.0565   0.6482   0.1023
  -1.250   0.2324   0.03120   0.02326  -0.0567   0.6417   0.1047
  -1.000   0.2715   0.02845   0.01975  -0.0563   0.6369   0.0586
  -0.750   0.2987   0.02676   0.01790  -0.0566   0.6297   0.0565
  -0.500   0.3270   0.02533   0.01617  -0.0565   0.6243   0.0550
  -0.250   0.3561   0.02407   0.01462  -0.0566   0.6174   0.0541
   0.000   0.3849   0.02313   0.01334  -0.0564   0.6115   0.0570
   0.250   0.4138   0.02242   0.01230  -0.0562   0.6052   0.0590
   0.500   0.4416   0.02147   0.01118  -0.0562   0.5988   0.0581
   0.750   0.4694   0.02070   0.01019  -0.0560   0.5935   0.0572
   1.000   0.4974   0.02006   0.00944  -0.0560   0.5865   0.0564
   1.250   0.5251   0.01949   0.00871  -0.0558   0.5812   0.0557
   1.500   0.5530   0.01904   0.00819  -0.0558   0.5745   0.0552
   1.750   0.5808   0.01863   0.00770  -0.0557   0.5686   0.0550
   2.000   0.6088   0.01833   0.00731  -0.0556   0.5628   0.0550
   2.250   0.6358   0.01812   0.00706  -0.0555   0.5565   0.0553
   2.500   0.6622   0.01798   0.00680  -0.0551   0.5517   0.0560
   2.750   0.6890   0.01797   0.00677  -0.0551   0.5448   0.0572
   3.000   0.7156   0.01796   0.00668  -0.0548   0.5393   0.0591
   3.250   0.7423   0.01800   0.00674  -0.0547   0.5336   0.0643
   3.500   0.7691   0.01807   0.00691  -0.0547   0.5277   0.0828
   4.000   0.8373   0.01698   0.00739  -0.0578   0.5161   1.0000
   4.250   0.8632   0.01721   0.00761  -0.0575   0.5108   1.0000
   4.500   0.8891   0.01748   0.00790  -0.0573   0.5056   1.0000
   4.750   0.9149   0.01779   0.00830  -0.0572   0.4999   1.0000
   5.000   0.9408   0.01805   0.00860  -0.0569   0.4955   1.0000
   5.250   0.9658   0.01802   0.00864  -0.0564   0.4812   1.0000
   5.500   0.9901   0.01794   0.00860  -0.0557   0.4606   1.0000
   5.750   1.0141   0.01790   0.00855  -0.0550   0.4362   1.0000
   6.000   1.0376   0.01807   0.00875  -0.0544   0.4046   1.0000
   6.250   1.0588   0.01854   0.00906  -0.0536   0.3461   1.0000
   6.500   1.0603   0.02195   0.01095  -0.0521   0.1084   1.0000
   6.750   1.0686   0.02448   0.01301  -0.0507   0.0310   1.0000
   7.000   1.0846   0.02579   0.01448  -0.0496   0.0256   1.0000
   7.250   1.0986   0.02721   0.01611  -0.0484   0.0232   1.0000
   7.500   1.1119   0.02859   0.01775  -0.0471   0.0223   1.0000
   7.750   1.1217   0.03019   0.01959  -0.0456   0.0215   1.0000
   8.000   1.1276   0.03200   0.02168  -0.0441   0.0207   1.0000
   8.250   1.1278   0.03405   0.02391  -0.0423   0.0197   1.0000
   8.500   1.1263   0.03648   0.02651  -0.0411   0.0187   1.0000
   8.750   1.1247   0.03915   0.02931  -0.0403   0.0179   1.0000
   9.000   1.1236   0.04182   0.03211  -0.0394   0.0174   1.0000
   9.250   1.1243   0.04429   0.03466  -0.0382   0.0171   1.0000
   9.500   1.1280   0.04636   0.03678  -0.0366   0.0167   1.0000
   9.750   1.1370   0.04789   0.03830  -0.0344   0.0164   1.0000
  10.000   1.1538   0.04897   0.03937  -0.0316   0.0161   1.0000
  10.250   1.1803   0.04993   0.04033  -0.0287   0.0159   1.0000
  10.500   1.0096   0.04807   0.03947  -0.0214   0.0168   1.0000
  10.750   1.0430   0.04807   0.03941  -0.0178   0.0164   1.0000
  11.000   1.0857   0.04891   0.04033  -0.0148   0.0157   1.0000
  11.250   1.1325   0.05319   0.04475  -0.0127   0.0142   1.0000
  11.500   1.1287   0.05635   0.04816  -0.0115   0.0140   1.0000
  11.750   1.1290   0.06010   0.05216  -0.0103   0.0140   1.0000
  12.000   1.1267   0.06418   0.05647  -0.0092   0.0141   1.0000
  12.250   1.1227   0.06864   0.06116  -0.0082   0.0142   1.0000
  12.750   1.2505   0.08243   0.07523  -0.0184   0.0150   1.0000
  13.000   1.2400   0.08605   0.07909  -0.0187   0.0152   1.0000
  13.250   1.2280   0.09004   0.08333  -0.0195   0.0154   1.0000
  13.500   1.2143   0.09451   0.08805  -0.0207   0.0157   1.0000
  13.750   1.1992   0.09949   0.09327  -0.0224   0.0160   1.0000
  14.000   1.1804   0.10519   0.09923  -0.0250   0.0162   1.0000
  14.250   1.1616   0.11134   0.10562  -0.0280   0.0165   1.0000
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