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NACA M19 AIRFOIL (m19-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M19 AIRFOIL (m19-il)
Reynolds number: 500,000
Max Cl/Cd: 82.98 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m19-il-500000-n5.txt
Download as CSV file: xf-m19-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3796   0.10170   0.09874   0.0107   0.6768   0.0067
  -7.500  -0.3729   0.09859   0.09562   0.0088   0.6701   0.0062
  -7.250  -0.3667   0.09533   0.09234   0.0066   0.6643   0.0059
  -7.000  -0.3559   0.09166   0.08866   0.0033   0.6582   0.0057
  -6.500  -0.3283   0.08417   0.08110  -0.0039   0.6470   0.0058
  -6.250  -0.3115   0.08043   0.07732  -0.0076   0.6413   0.0062
  -6.000  -0.2915   0.07583   0.07264  -0.0124   0.6364   0.0069
  -5.750  -0.2716   0.07191   0.06867  -0.0163   0.6310   0.0069
  -5.500  -0.2498   0.06793   0.06462  -0.0202   0.6257   0.0068
  -5.250  -0.2257   0.06366   0.06027  -0.0242   0.6208   0.0069
  -5.000  -0.1992   0.05892   0.05544  -0.0285   0.6158   0.0071
  -4.750  -0.1738   0.05564   0.05206  -0.0316   0.6106   0.0075
  -4.500  -0.1479   0.05301   0.04935  -0.0340   0.6053   0.0079
  -4.250  -0.1205   0.05018   0.04641  -0.0365   0.5998   0.0091
  -4.000  -0.0882   0.04506   0.04110  -0.0401   0.5954   0.0101
  -3.750  -0.0577   0.04105   0.03693  -0.0426   0.5907   0.0109
  -3.500  -0.0313   0.03967   0.03544  -0.0437   0.5849   0.0117
  -3.250  -0.0030   0.03770   0.03334  -0.0449   0.5797   0.0135
  -3.000   0.0358   0.03107   0.02631  -0.0471   0.5758   0.0163
  -2.750   0.0603   0.03088   0.02607  -0.0476   0.5697   0.0171
  -2.500   0.0860   0.03024   0.02535  -0.0481   0.5643   0.0183
  -2.250   0.1149   0.02834   0.02328  -0.0487   0.5589   0.0196
  -2.000   0.1447   0.02625   0.02097  -0.0491   0.5536   0.0212
  -1.750   0.1760   0.02400   0.01847  -0.0493   0.5488   0.0234
  -1.500   0.2066   0.02141   0.01557  -0.0493   0.5437   0.0254
  -1.250   0.2338   0.02006   0.01404  -0.0496   0.5382   0.0262
  -1.000   0.2602   0.01977   0.01370  -0.0500   0.5326   0.0278
  -0.750   0.2884   0.01867   0.01244  -0.0501   0.5271   0.0290
  -0.250   0.3471   0.01455   0.00762  -0.0496   0.5174   0.0276
   0.000   0.3753   0.01380   0.00669  -0.0497   0.5115   0.0288
   0.250   0.4034   0.01321   0.00596  -0.0498   0.5061   0.0304
   0.500   0.4316   0.01268   0.00530  -0.0498   0.5006   0.0314
   0.750   0.4596   0.01226   0.00474  -0.0499   0.4953   0.0320
   1.000   0.4876   0.01189   0.00430  -0.0499   0.4901   0.0325
   1.250   0.5156   0.01170   0.00404  -0.0500   0.4842   0.0336
   1.500   0.5434   0.01146   0.00373  -0.0501   0.4787   0.0339
   1.750   0.5711   0.01107   0.00330  -0.0501   0.4730   0.0334
   2.000   0.5987   0.01080   0.00299  -0.0501   0.4677   0.0330
   2.250   0.6262   0.01059   0.00276  -0.0502   0.4628   0.0326
   2.500   0.6538   0.01042   0.00259  -0.0502   0.4574   0.0322
   2.750   0.6812   0.01032   0.00246  -0.0502   0.4515   0.0319
   3.000   0.7089   0.01023   0.00239  -0.0503   0.4450   0.0317
   3.250   0.7364   0.01020   0.00236  -0.0504   0.4383   0.0315
   3.500   0.7641   0.01019   0.00235  -0.0505   0.4318   0.0313
   3.750   0.7918   0.01021   0.00237  -0.0507   0.4257   0.0312
   4.000   0.8193   0.01027   0.00241  -0.0508   0.4138   0.0312
   4.250   0.8465   0.01041   0.00249  -0.0509   0.3959   0.0313
   4.500   0.8736   0.01060   0.00260  -0.0511   0.3729   0.0318
   4.750   0.9003   0.01085   0.00276  -0.0512   0.3483   0.0325
   5.000   0.9252   0.01152   0.00310  -0.0513   0.2832   0.0344
   5.250   0.9391   0.01448   0.00498  -0.0512   0.0224   0.1268
   5.750   0.9988   0.01381   0.00600  -0.0531   0.0128   1.0000
   6.000   1.0235   0.01424   0.00651  -0.0528   0.0111   1.0000
   6.250   1.0472   0.01481   0.00717  -0.0525   0.0091   1.0000
   6.500   1.0693   0.01565   0.00813  -0.0520   0.0081   1.0000
   6.750   1.0920   0.01632   0.00888  -0.0516   0.0075   1.0000
   7.000   1.1132   0.01715   0.00980  -0.0510   0.0069   1.0000
   7.250   1.1336   0.01801   0.01073  -0.0504   0.0063   1.0000
   7.500   1.1543   0.01872   0.01150  -0.0499   0.0057   1.0000
   7.750   1.1680   0.02020   0.01306  -0.0487   0.0051   1.0000
   8.000   1.1841   0.02130   0.01426  -0.0477   0.0049   1.0000
   8.250   1.1965   0.02265   0.01572  -0.0463   0.0047   1.0000
   8.500   1.2056   0.02419   0.01736  -0.0446   0.0045   1.0000
   8.750   1.2100   0.02584   0.01911  -0.0425   0.0043   1.0000
   9.000   1.2135   0.02772   0.02108  -0.0407   0.0041   1.0000
   9.250   1.2191   0.02963   0.02308  -0.0392   0.0040   1.0000
   9.500   1.2268   0.03146   0.02502  -0.0375   0.0039   1.0000
   9.750   1.2372   0.03320   0.02682  -0.0356   0.0039   1.0000
  10.000   1.2495   0.03482   0.02853  -0.0340   0.0037   1.0000
  10.250   1.2605   0.03638   0.03016  -0.0330   0.0036   1.0000
  10.500   1.2690   0.03803   0.03189  -0.0324   0.0034   1.0000
  10.750   1.2769   0.04001   0.03396  -0.0314   0.0032   1.0000
  11.000   1.2907   0.04213   0.03628  -0.0293   0.0030   1.0000
  11.250   1.3037   0.04468   0.03905  -0.0274   0.0028   1.0000
  11.500   1.3127   0.04768   0.04228  -0.0256   0.0027   1.0000
  11.750   1.3172   0.05098   0.04582  -0.0241   0.0026   1.0000
  12.000   1.3160   0.05448   0.04954  -0.0230   0.0026   1.0000
  12.250   1.3109   0.05826   0.05355  -0.0221   0.0025   1.0000
  12.500   1.3031   0.06224   0.05774  -0.0216   0.0025   1.0000
  12.750   1.2932   0.06646   0.06217  -0.0214   0.0025   1.0000
  13.000   1.2816   0.07097   0.06687  -0.0217   0.0025   1.0000
  13.250   1.2684   0.07571   0.07180  -0.0223   0.0025   1.0000
  13.500   1.2538   0.08078   0.07704  -0.0233   0.0025   1.0000
  13.750   1.2384   0.08608   0.08251  -0.0248   0.0025   1.0000
  14.000   1.2221   0.09171   0.08830  -0.0266   0.0025   1.0000
  14.250   1.2055   0.09773   0.09448  -0.0290   0.0026   1.0000
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