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NACA M2 (nacam2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M2 (nacam2-il)
Reynolds number: 500,000
Max Cl/Cd: 54.44 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam2-il-500000-n5.txt
Download as CSV file: xf-nacam2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.9456   0.10000   0.09779   0.0149   1.0000   0.0066
 -13.250  -1.0975   0.05672   0.05415  -0.0147   1.0000   0.0056
 -13.000  -1.1256   0.04840   0.04557  -0.0208   1.0000   0.0056
 -12.750  -1.1456   0.04343   0.04035  -0.0218   1.0000   0.0056
 -12.500  -1.1594   0.03998   0.03667  -0.0201   1.0000   0.0057
 -12.250  -1.1668   0.03717   0.03361  -0.0177   1.0000   0.0057
 -12.000  -1.1657   0.03453   0.03071  -0.0159   1.0000   0.0059
 -11.750  -1.1595   0.03221   0.02812  -0.0143   1.0000   0.0060
 -11.500  -1.1492   0.03021   0.02586  -0.0129   1.0000   0.0062
 -11.250  -1.1357   0.02849   0.02387  -0.0118   1.0000   0.0064
 -11.000  -1.1222   0.02666   0.02180  -0.0105   1.0000   0.0067
 -10.750  -1.1060   0.02518   0.02016  -0.0095   1.0000   0.0070
 -10.500  -1.0868   0.02407   0.01891  -0.0087   1.0000   0.0074
 -10.250  -1.0668   0.02301   0.01771  -0.0080   1.0000   0.0077
 -10.000  -1.0462   0.02196   0.01650  -0.0072   1.0000   0.0081
  -9.750  -1.0252   0.02093   0.01531  -0.0065   1.0000   0.0085
  -9.500  -1.0036   0.01995   0.01417  -0.0058   1.0000   0.0089
  -9.250  -0.9813   0.01907   0.01313  -0.0052   1.0000   0.0093
  -9.000  -0.9593   0.01810   0.01204  -0.0045   1.0000   0.0102
  -8.750  -0.9352   0.01756   0.01146  -0.0042   1.0000   0.0111
  -8.500  -0.9107   0.01706   0.01089  -0.0038   1.0000   0.0121
  -8.250  -0.8864   0.01649   0.01021  -0.0034   1.0000   0.0130
  -8.000  -0.8623   0.01584   0.00951  -0.0029   1.0000   0.0143
  -7.750  -0.8367   0.01554   0.00921  -0.0027   1.0000   0.0157
  -7.500  -0.8110   0.01524   0.00887  -0.0024   1.0000   0.0173
  -7.250  -0.7852   0.01497   0.00851  -0.0021   1.0000   0.0189
  -7.000  -0.7598   0.01459   0.00807  -0.0018   1.0000   0.0200
  -6.750  -0.7350   0.01408   0.00754  -0.0014   1.0000   0.0218
  -6.500  -0.7092   0.01381   0.00725  -0.0012   1.0000   0.0234
  -6.250  -0.6835   0.01352   0.00692  -0.0009   1.0000   0.0251
  -6.000  -0.6580   0.01319   0.00653  -0.0005   1.0000   0.0266
  -5.750  -0.6324   0.01292   0.00621  -0.0002   1.0000   0.0277
  -5.500  -0.6067   0.01268   0.00593   0.0002   1.0000   0.0283
  -5.250  -0.5826   0.01212   0.00532   0.0008   1.0000   0.0295
  -5.000  -0.5586   0.01158   0.00473   0.0015   1.0000   0.0313
  -4.750  -0.5342   0.01120   0.00432   0.0021   1.0000   0.0327
  -4.500  -0.5096   0.01089   0.00400   0.0027   1.0000   0.0342
  -4.250  -0.4851   0.01061   0.00369   0.0033   1.0000   0.0354
  -4.000  -0.4606   0.01036   0.00340   0.0039   1.0000   0.0365
  -3.750  -0.4361   0.01014   0.00316   0.0046   1.0000   0.0375
  -3.500  -0.4118   0.00995   0.00294   0.0053   1.0000   0.0384
  -3.250  -0.3796   0.00975   0.00272   0.0042   0.9975   0.0394
  -3.000  -0.3452   0.00952   0.00249   0.0027   0.9947   0.0431
  -2.750  -0.3119   0.00929   0.00230   0.0014   0.9907   0.0497
  -2.500  -0.2785   0.00892   0.00210   0.0000   0.9870   0.0867
  -2.250  -0.2469   0.00845   0.00192  -0.0012   0.9818   0.1529
  -2.000  -0.2152   0.00795   0.00175  -0.0024   0.9762   0.2372
  -1.750  -0.1847   0.00751   0.00162  -0.0032   0.9688   0.3174
  -1.500  -0.1542   0.00703   0.00151  -0.0041   0.9609   0.4131
  -1.000  -0.0970   0.00631   0.00135  -0.0044   0.9310   0.5705
  -0.750  -0.0718   0.00597   0.00131  -0.0037   0.9111   0.6551
  -0.500  -0.0471   0.00572   0.00130  -0.0028   0.8927   0.7245
  -0.250  -0.0228   0.00557   0.00130  -0.0016   0.8685   0.7787
   0.000   0.0000   0.00551   0.00130   0.0000   0.8298   0.8293
   0.250   0.0229   0.00557   0.00130   0.0016   0.7800   0.8684
   0.500   0.0471   0.00572   0.00130   0.0028   0.7243   0.8927
   0.750   0.0717   0.00597   0.00131   0.0037   0.6544   0.9111
   1.000   0.0970   0.00631   0.00135   0.0044   0.5715   0.9310
   1.250   0.1240   0.00670   0.00142   0.0046   0.4822   0.9490
   1.500   0.1541   0.00702   0.00151   0.0041   0.4142   0.9609
   1.750   0.1846   0.00752   0.00162   0.0032   0.3159   0.9688
   2.000   0.2152   0.00795   0.00175   0.0024   0.2359   0.9762
   2.250   0.2469   0.00845   0.00192   0.0012   0.1532   0.9819
   2.500   0.2785   0.00892   0.00210   0.0000   0.0866   0.9870
   2.750   0.3119   0.00929   0.00230  -0.0014   0.0497   0.9907
   3.000   0.3451   0.00952   0.00249  -0.0027   0.0432   0.9947
   3.250   0.3795   0.00975   0.00272  -0.0042   0.0394   0.9975
   3.500   0.4117   0.00995   0.00294  -0.0053   0.0384   1.0000
   3.750   0.4361   0.01014   0.00316  -0.0046   0.0375   1.0000
   4.000   0.4605   0.01036   0.00340  -0.0039   0.0365   1.0000
   4.250   0.4851   0.01061   0.00369  -0.0033   0.0355   1.0000
   4.500   0.5096   0.01089   0.00400  -0.0027   0.0342   1.0000
   4.750   0.5341   0.01120   0.00432  -0.0021   0.0327   1.0000
   5.000   0.5586   0.01158   0.00473  -0.0015   0.0313   1.0000
   5.250   0.5826   0.01212   0.00531  -0.0008   0.0295   1.0000
   5.500   0.6067   0.01268   0.00593  -0.0002   0.0283   1.0000
   5.750   0.6323   0.01292   0.00621   0.0002   0.0277   1.0000
   6.000   0.6580   0.01319   0.00653   0.0005   0.0266   1.0000
   6.250   0.6835   0.01352   0.00692   0.0009   0.0251   1.0000
   6.500   0.7092   0.01381   0.00725   0.0012   0.0234   1.0000
   6.750   0.7350   0.01408   0.00754   0.0014   0.0218   1.0000
   7.000   0.7598   0.01459   0.00807   0.0018   0.0200   1.0000
   7.250   0.7852   0.01497   0.00851   0.0021   0.0189   1.0000
   7.500   0.8110   0.01525   0.00888   0.0024   0.0173   1.0000
   7.750   0.8367   0.01554   0.00921   0.0027   0.0157   1.0000
   8.000   0.8623   0.01584   0.00951   0.0029   0.0143   1.0000
   8.250   0.8864   0.01649   0.01022   0.0034   0.0130   1.0000
   8.500   0.9107   0.01706   0.01089   0.0038   0.0121   1.0000
   8.750   0.9352   0.01756   0.01145   0.0041   0.0111   1.0000
   9.000   0.9594   0.01810   0.01204   0.0045   0.0102   1.0000
   9.250   0.9814   0.01907   0.01313   0.0052   0.0093   1.0000
   9.500   1.0037   0.01995   0.01417   0.0058   0.0089   1.0000
   9.750   1.0253   0.02092   0.01530   0.0065   0.0085   1.0000
  10.000   1.0463   0.02195   0.01650   0.0072   0.0081   1.0000
  10.250   1.0669   0.02300   0.01770   0.0080   0.0077   1.0000
  10.500   1.0870   0.02406   0.01890   0.0087   0.0074   1.0000
  10.750   1.1062   0.02517   0.02015   0.0095   0.0070   1.0000
  11.000   1.1223   0.02667   0.02181   0.0105   0.0067   1.0000
  11.250   1.1360   0.02848   0.02385   0.0117   0.0064   1.0000
  11.500   1.1494   0.03021   0.02586   0.0129   0.0062   1.0000
  11.750   1.1598   0.03221   0.02812   0.0143   0.0060   1.0000
  12.000   1.1660   0.03454   0.03071   0.0158   0.0059   1.0000
  12.250   1.1672   0.03717   0.03361   0.0176   0.0057   1.0000
  12.500   1.1598   0.04000   0.03669   0.0200   0.0057   1.0000
  12.750   1.1460   0.04346   0.04038   0.0217   0.0056   1.0000
  13.000   1.1266   0.04837   0.04554   0.0207   0.0056   1.0000
  13.250   1.0976   0.05688   0.05432   0.0144   0.0056   1.0000
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