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NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M14 AIRFOIL (m14-il)
Reynolds number: 50,000
Max Cl/Cd: 38.85 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m14-il-50000-n5.txt
Download as CSV file: xf-m14-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3153   0.11383   0.10730  -0.0198   1.0000   0.0975
  -9.500  -0.3224   0.11206   0.10560  -0.0218   1.0000   0.0996
  -9.250  -0.4189   0.11768   0.11078  -0.0106   1.0000   0.0904
  -9.000  -0.4134   0.11450   0.10763  -0.0117   1.0000   0.0949
  -8.750  -0.4148   0.11237   0.10558  -0.0145   1.0000   0.0988
  -8.500  -0.4223   0.11107   0.10440  -0.0188   1.0000   0.1001
  -8.250  -0.4283   0.10941   0.10284  -0.0242   1.0000   0.1006
  -8.000  -0.4006   0.10168   0.09505  -0.0179   1.0000   0.1050
  -7.750  -0.3962   0.09851   0.09194  -0.0188   1.0000   0.1084
  -7.500  -0.3958   0.09580   0.08931  -0.0216   1.0000   0.1123
  -7.250  -0.3985   0.09414   0.08769  -0.0294   1.0000   0.1150
  -7.000  -0.3874   0.08901   0.08264  -0.0268   1.0000   0.1178
  -6.750  -0.3785   0.08575   0.07938  -0.0265   1.0000   0.1249
  -6.500  -0.3769   0.08396   0.07757  -0.0342   1.0000   0.1304
  -6.250  -0.3663   0.07929   0.07300  -0.0299   1.0000   0.1348
  -6.000  -0.3593   0.07643   0.07016  -0.0310   1.0000   0.1406
  -5.500  -0.3480   0.07052   0.06429  -0.0319   1.0000   0.1495
  -5.250  -0.3420   0.06932   0.06293  -0.0352   1.0000   0.1600
  -5.000  -0.3386   0.06561   0.05935  -0.0321   1.0000   0.1623
  -4.750  -0.3347   0.06339   0.05715  -0.0302   1.0000   0.1701
  -4.250  -0.2570   0.05175   0.04434  -0.0434   0.9875   0.0842
  -4.000  -0.2221   0.04780   0.04015  -0.0471   0.9776   0.0803
  -3.750  -0.1836   0.04391   0.03581  -0.0512   0.9675   0.0765
  -3.500  -0.1456   0.04089   0.03238  -0.0547   0.9575   0.0774
  -3.250  -0.1047   0.03808   0.02912  -0.0583   0.9492   0.0789
  -3.000  -0.0676   0.03543   0.02596  -0.0608   0.9386   0.0773
  -2.750  -0.0293   0.03306   0.02308  -0.0631   0.9290   0.0760
  -2.500   0.0105   0.03097   0.02050  -0.0654   0.9205   0.0754
  -2.250   0.0450   0.02934   0.01848  -0.0667   0.9093   0.0754
  -2.000   0.0800   0.02794   0.01671  -0.0679   0.8986   0.0759
  -1.750   0.1162   0.02676   0.01524  -0.0693   0.8890   0.0779
  -1.500   0.1500   0.02588   0.01409  -0.0701   0.8781   0.0827
  -1.250   0.1826   0.02512   0.01302  -0.0705   0.8667   0.0860
  -1.000   0.2156   0.02430   0.01208  -0.0711   0.8559   0.0885
  -0.750   0.2474   0.02365   0.01130  -0.0714   0.8455   0.0919
  -0.500   0.2765   0.02315   0.01066  -0.0712   0.8343   0.0964
  -0.250   0.3034   0.02276   0.01017  -0.0708   0.8223   0.1025
   0.000   0.3302   0.02242   0.00979  -0.0703   0.8108   0.1138
   0.250   0.3571   0.02195   0.00947  -0.0699   0.8000   0.1457
   0.750   0.4277   0.01967   0.00901  -0.0722   0.7784   1.0000
   1.000   0.4528   0.01989   0.00900  -0.0714   0.7668   1.0000
   1.250   0.4783   0.02010   0.00901  -0.0707   0.7559   1.0000
   1.500   0.5038   0.02030   0.00905  -0.0700   0.7451   1.0000
   1.750   0.5283   0.02059   0.00924  -0.0693   0.7332   1.0000
   2.000   0.5533   0.02087   0.00941  -0.0687   0.7219   1.0000
   2.250   0.5790   0.02111   0.00956  -0.0680   0.7117   1.0000
   2.500   0.6043   0.02138   0.00978  -0.0674   0.7010   1.0000
   2.750   0.6286   0.02173   0.01011  -0.0668   0.6895   1.0000
   3.000   0.6536   0.02206   0.01041  -0.0662   0.6789   1.0000
   3.250   0.6797   0.02228   0.01060  -0.0655   0.6697   1.0000
   3.500   0.7036   0.02270   0.01108  -0.0649   0.6581   1.0000
   3.750   0.7278   0.02310   0.01153  -0.0643   0.6472   1.0000
   4.000   0.7531   0.02343   0.01189  -0.0637   0.6373   1.0000
   4.250   0.7779   0.02379   0.01234  -0.0631   0.6272   1.0000
   4.500   0.8016   0.02427   0.01292  -0.0625   0.6159   1.0000
   4.750   0.8260   0.02470   0.01345  -0.0618   0.6057   1.0000
   5.000   0.8517   0.02501   0.01387  -0.0612   0.5965   1.0000
   5.250   0.8746   0.02557   0.01461  -0.0605   0.5849   1.0000
   5.500   0.8982   0.02611   0.01530  -0.0599   0.5742   1.0000
   5.750   0.9233   0.02649   0.01582  -0.0592   0.5646   1.0000
   6.000   0.9469   0.02702   0.01658  -0.0585   0.5538   1.0000
   6.250   0.9693   0.02764   0.01743  -0.0577   0.5422   1.0000
   6.500   0.9925   0.02818   0.01820  -0.0569   0.5309   1.0000
   6.750   1.0163   0.02857   0.01881  -0.0559   0.5191   1.0000
   7.000   1.0398   0.02889   0.01940  -0.0548   0.5056   1.0000
   7.250   1.0607   0.02919   0.01997  -0.0533   0.4880   1.0000
   7.500   1.0791   0.02864   0.01954  -0.0505   0.4559   1.0000
   7.750   1.0889   0.02803   0.01879  -0.0465   0.3972   1.0000
   8.000   1.0948   0.02852   0.01899  -0.0430   0.3238   1.0000
   8.250   1.0961   0.03011   0.02005  -0.0396   0.2188   1.0000
   8.500   1.0857   0.03327   0.02237  -0.0362   0.1262   1.0000
   8.750   1.0782   0.03636   0.02508  -0.0332   0.0909   1.0000
   9.000   1.0724   0.03903   0.02764  -0.0304   0.0764   1.0000
   9.250   1.0673   0.04185   0.03043  -0.0284   0.0681   1.0000
   9.500   1.0659   0.04453   0.03323  -0.0268   0.0621   1.0000
   9.750   1.0645   0.04734   0.03613  -0.0255   0.0583   1.0000
  10.000   1.0621   0.05033   0.03916  -0.0244   0.0553   1.0000
  10.250   1.0659   0.05277   0.04178  -0.0231   0.0519   1.0000
  10.500   1.0714   0.05510   0.04427  -0.0218   0.0482   1.0000
  10.750   1.0777   0.05738   0.04662  -0.0204   0.0451   1.0000
  11.000   1.0950   0.05893   0.04816  -0.0178   0.0427   1.0000
  11.250   1.1188   0.06044   0.05008  -0.0156   0.0406   1.0000
  11.500   1.1343   0.06276   0.05270  -0.0142   0.0383   1.0000
  11.750   1.1437   0.06548   0.05566  -0.0133   0.0364   1.0000
  12.000   1.1506   0.06847   0.05884  -0.0125   0.0350   1.0000
  12.250   1.1567   0.07185   0.06242  -0.0117   0.0342   1.0000
  12.500   1.1592   0.07567   0.06648  -0.0112   0.0337   1.0000
  12.750   1.1569   0.07995   0.07100  -0.0111   0.0333   1.0000
  13.000   1.1487   0.08456   0.07582  -0.0115   0.0332   1.0000
  13.250   1.1363   0.08952   0.08106  -0.0126   0.0332   1.0000
  13.500   1.1225   0.09484   0.08662  -0.0142   0.0332   1.0000
  14.000   1.0884   0.10699   0.09929  -0.0198   0.0334   1.0000
  14.250   1.0656   0.11464   0.10719  -0.0245   0.0338   1.0000
  14.500   1.0381   0.12441   0.11719  -0.0312   0.0345   1.0000
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