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NACA M2 AIRFOIL (m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M2 AIRFOIL (m2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.59 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m2-il-1000000.txt
Download as CSV file: xf-m2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -1.1523   0.05335   0.05139  -0.0155   1.0000   0.0075
 -13.250  -1.1847   0.04573   0.04351  -0.0194   1.0000   0.0075
 -13.000  -1.2064   0.04120   0.03873  -0.0185   1.0000   0.0075
 -12.750  -1.2207   0.03792   0.03523  -0.0157   1.0000   0.0076
 -12.500  -1.2226   0.03500   0.03205  -0.0139   1.0000   0.0077
 -12.250  -1.2172   0.03259   0.02941  -0.0123   1.0000   0.0078
 -12.000  -1.2066   0.03065   0.02726  -0.0111   1.0000   0.0079
 -11.750  -1.1921   0.02911   0.02554  -0.0101   1.0000   0.0081
 -11.500  -1.1892   0.02551   0.02150  -0.0080   1.0000   0.0084
 -11.250  -1.1755   0.02347   0.01925  -0.0068   1.0000   0.0088
 -11.000  -1.1547   0.02255   0.01824  -0.0062   1.0000   0.0091
 -10.750  -1.1320   0.02192   0.01754  -0.0058   1.0000   0.0094
 -10.500  -1.1086   0.02135   0.01689  -0.0055   1.0000   0.0098
 -10.250  -1.0857   0.02062   0.01606  -0.0050   1.0000   0.0103
 -10.000  -1.0627   0.01983   0.01515  -0.0046   1.0000   0.0107
  -9.750  -1.0391   0.01910   0.01430  -0.0042   1.0000   0.0110
  -9.500  -1.0188   0.01760   0.01259  -0.0034   1.0000   0.0115
  -9.250  -0.9956   0.01673   0.01165  -0.0030   1.0000   0.0123
  -9.000  -0.9697   0.01640   0.01130  -0.0029   1.0000   0.0128
  -8.750  -0.9439   0.01604   0.01090  -0.0027   1.0000   0.0135
  -8.500  -0.9182   0.01562   0.01041  -0.0025   1.0000   0.0142
  -8.250  -0.8919   0.01528   0.01001  -0.0024   1.0000   0.0148
  -8.000  -0.8681   0.01434   0.00898  -0.0020   1.0000   0.0158
  -7.750  -0.8417   0.01406   0.00871  -0.0020   1.0000   0.0167
  -7.500  -0.8148   0.01385   0.00849  -0.0019   1.0000   0.0176
  -7.250  -0.7882   0.01355   0.00815  -0.0019   1.0000   0.0187
  -7.000  -0.7612   0.01333   0.00789  -0.0018   1.0000   0.0195
  -6.750  -0.7336   0.01328   0.00781  -0.0018   1.0000   0.0200
  -6.500  -0.7106   0.01203   0.00649  -0.0013   1.0000   0.0220
  -6.250  -0.6840   0.01176   0.00623  -0.0012   1.0000   0.0233
  -6.000  -0.6576   0.01144   0.00588  -0.0010   1.0000   0.0245
  -5.750  -0.6315   0.01113   0.00554  -0.0008   1.0000   0.0256
  -5.500  -0.6053   0.01095   0.00534  -0.0005   1.0000   0.0264
  -5.250  -0.5810   0.01050   0.00485   0.0001   1.0000   0.0273
  -5.000  -0.5583   0.00983   0.00411   0.0010   1.0000   0.0292
  -4.750  -0.5347   0.00948   0.00374   0.0017   1.0000   0.0306
  -4.500  -0.5109   0.00922   0.00347   0.0025   1.0000   0.0321
  -4.250  -0.4871   0.00897   0.00320   0.0033   1.0000   0.0332
  -4.000  -0.4632   0.00876   0.00297   0.0040   1.0000   0.0342
  -3.750  -0.4300   0.00855   0.00273   0.0028   0.9985   0.0352
  -3.500  -0.3955   0.00828   0.00244   0.0012   0.9967   0.0369
  -3.250  -0.3597   0.00801   0.00218  -0.0006   0.9950   0.0413
  -3.000  -0.3232   0.00769   0.00196  -0.0026   0.9928   0.0589
  -2.750  -0.2898   0.00744   0.00188  -0.0039   0.9898   0.0923
  -2.500  -0.2552   0.00731   0.00179  -0.0055   0.9855   0.1024
  -2.250  -0.2238   0.00721   0.00171  -0.0062   0.9780   0.1093
  -2.000  -0.1956   0.00711   0.00164  -0.0061   0.9705   0.1178
  -1.750  -0.1699   0.00701   0.00157  -0.0055   0.9622   0.1256
  -1.500  -0.1449   0.00685   0.00150  -0.0048   0.9534   0.1471
  -1.250  -0.1229   0.00593   0.00129  -0.0040   0.9425   0.3616
  -1.000  -0.0979   0.00549   0.00120  -0.0035   0.9302   0.4623
  -0.750  -0.0731   0.00508   0.00113  -0.0028   0.9138   0.5592
  -0.500  -0.0490   0.00476   0.00104  -0.0019   0.8800   0.6437
  -0.250  -0.0250   0.00462   0.00098  -0.0008   0.8326   0.7142
   0.000   0.0000   0.00458   0.00097   0.0000   0.7811   0.7798
   0.250   0.0250   0.00462   0.00098   0.0008   0.7137   0.8326
   0.500   0.0491   0.00476   0.00104   0.0018   0.6444   0.8798
   0.750   0.0731   0.00508   0.00113   0.0028   0.5589   0.9137
   1.000   0.0979   0.00549   0.00120   0.0034   0.4623   0.9301
   1.250   0.1230   0.00591   0.00129   0.0040   0.3646   0.9425
   1.500   0.1449   0.00685   0.00150   0.0048   0.1473   0.9536
   1.750   0.1699   0.00701   0.00157   0.0055   0.1256   0.9622
   2.000   0.1956   0.00711   0.00164   0.0061   0.1178   0.9706
   2.250   0.2238   0.00721   0.00171   0.0062   0.1093   0.9781
   2.500   0.2551   0.00731   0.00179   0.0055   0.1024   0.9855
   2.750   0.2899   0.00744   0.00188   0.0039   0.0923   0.9898
   3.000   0.3233   0.00769   0.00196   0.0026   0.0589   0.9928
   3.250   0.3598   0.00801   0.00218   0.0006   0.0413   0.9950
   3.500   0.3955   0.00828   0.00244  -0.0012   0.0369   0.9967
   3.750   0.4300   0.00855   0.00273  -0.0028   0.0352   0.9985
   4.000   0.4631   0.00876   0.00297  -0.0040   0.0342   1.0000
   4.250   0.4870   0.00897   0.00320  -0.0033   0.0332   1.0000
   4.500   0.5108   0.00922   0.00347  -0.0025   0.0321   1.0000
   4.750   0.5346   0.00948   0.00375  -0.0017   0.0306   1.0000
   5.000   0.5582   0.00983   0.00411  -0.0010   0.0291   1.0000
   5.250   0.5810   0.01049   0.00483  -0.0001   0.0274   1.0000
   5.500   0.6053   0.01096   0.00535   0.0005   0.0264   1.0000
   5.750   0.6314   0.01113   0.00554   0.0008   0.0256   1.0000
   6.000   0.6576   0.01144   0.00588   0.0010   0.0245   1.0000
   6.250   0.6840   0.01176   0.00622   0.0012   0.0232   1.0000
   6.500   0.7106   0.01204   0.00650   0.0013   0.0220   1.0000
   6.750   0.7337   0.01328   0.00781   0.0018   0.0200   1.0000
   7.000   0.7612   0.01333   0.00789   0.0018   0.0195   1.0000
   7.250   0.7882   0.01357   0.00817   0.0019   0.0187   1.0000
   7.500   0.8149   0.01385   0.00849   0.0019   0.0176   1.0000
   7.750   0.8417   0.01407   0.00871   0.0020   0.0167   1.0000
   8.000   0.8682   0.01433   0.00897   0.0020   0.0158   1.0000
   8.250   0.8920   0.01529   0.01003   0.0024   0.0148   1.0000
   8.500   0.9183   0.01561   0.01041   0.0025   0.0142   1.0000
   8.750   0.9440   0.01604   0.01089   0.0027   0.0135   1.0000
   9.000   0.9698   0.01640   0.01130   0.0029   0.0128   1.0000
   9.250   0.9956   0.01674   0.01165   0.0030   0.0123   1.0000
   9.500   1.0188   0.01761   0.01260   0.0034   0.0115   1.0000
   9.750   1.0392   0.01910   0.01430   0.0042   0.0110   1.0000
  10.000   1.0629   0.01982   0.01513   0.0046   0.0107   1.0000
  10.250   1.0858   0.02061   0.01605   0.0050   0.0103   1.0000
  10.500   1.1089   0.02133   0.01687   0.0054   0.0098   1.0000
  10.750   1.1321   0.02191   0.01753   0.0058   0.0094   1.0000
  11.000   1.1549   0.02254   0.01822   0.0062   0.0091   1.0000
  11.250   1.1757   0.02346   0.01923   0.0067   0.0088   1.0000
  11.500   1.1892   0.02554   0.02154   0.0080   0.0084   1.0000
  11.750   1.1928   0.02904   0.02546   0.0100   0.0081   1.0000
  12.000   1.2073   0.03059   0.02720   0.0110   0.0079   1.0000
  12.250   1.2176   0.03258   0.02940   0.0123   0.0078   1.0000
  12.500   1.2229   0.03501   0.03206   0.0138   0.0077   1.0000
  12.750   1.2213   0.03791   0.03522   0.0156   0.0075   1.0000
  13.000   1.2079   0.04112   0.03865   0.0183   0.0075   1.0000
  13.250   1.1869   0.04558   0.04335   0.0193   0.0075   1.0000
  13.500   1.1548   0.05310   0.05113   0.0156   0.0075   1.0000
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