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NACA M2 AIRFOIL (m2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M2 AIRFOIL (m2-il)
Reynolds number: 500,000
Max Cl/Cd: 54.37 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m2-il-500000-n5.txt
Download as CSV file: xf-m2-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -1.1224   0.05222   0.04966  -0.0173   1.0000   0.0057
 -12.750  -1.1497   0.04597   0.04313  -0.0186   1.0000   0.0057
 -12.500  -1.1677   0.04185   0.03875  -0.0169   1.0000   0.0057
 -12.250  -1.1749   0.03847   0.03508  -0.0149   1.0000   0.0058
 -12.000  -1.1738   0.03547   0.03180  -0.0134   1.0000   0.0059
 -11.750  -1.1673   0.03291   0.02896  -0.0120   1.0000   0.0061
 -11.500  -1.1565   0.03074   0.02652  -0.0108   1.0000   0.0063
 -11.250  -1.1424   0.02892   0.02440  -0.0098   1.0000   0.0065
 -11.000  -1.1283   0.02699   0.02224  -0.0087   1.0000   0.0067
 -10.750  -1.1116   0.02541   0.02048  -0.0078   1.0000   0.0071
 -10.500  -1.0919   0.02423   0.01915  -0.0072   1.0000   0.0074
 -10.250  -1.0713   0.02313   0.01790  -0.0066   1.0000   0.0078
 -10.000  -1.0502   0.02204   0.01665  -0.0060   1.0000   0.0082
  -9.750  -1.0286   0.02098   0.01543  -0.0054   1.0000   0.0086
  -9.500  -1.0063   0.02000   0.01427  -0.0049   1.0000   0.0090
  -9.250  -0.9835   0.01907   0.01319  -0.0044   1.0000   0.0095
  -9.000  -0.9607   0.01813   0.01213  -0.0039   1.0000   0.0104
  -8.750  -0.9360   0.01758   0.01153  -0.0036   1.0000   0.0113
  -8.500  -0.9111   0.01706   0.01094  -0.0034   1.0000   0.0123
  -8.250  -0.8863   0.01647   0.01025  -0.0031   1.0000   0.0133
  -8.000  -0.8615   0.01584   0.00958  -0.0028   1.0000   0.0147
  -7.750  -0.8355   0.01552   0.00925  -0.0026   1.0000   0.0161
  -7.500  -0.8095   0.01520   0.00888  -0.0025   1.0000   0.0178
  -7.250  -0.7831   0.01493   0.00853  -0.0024   1.0000   0.0193
  -7.000  -0.7578   0.01442   0.00795  -0.0021   1.0000   0.0206
  -6.750  -0.7323   0.01395   0.00745  -0.0019   1.0000   0.0223
  -6.500  -0.7062   0.01364   0.00712  -0.0017   1.0000   0.0240
  -6.250  -0.6801   0.01331   0.00674  -0.0016   1.0000   0.0257
  -6.000  -0.6542   0.01297   0.00633  -0.0013   1.0000   0.0271
  -5.750  -0.6281   0.01269   0.00600  -0.0011   1.0000   0.0281
  -5.500  -0.6022   0.01242   0.00569  -0.0008   1.0000   0.0287
  -5.250  -0.5777   0.01186   0.00508  -0.0003   1.0000   0.0301
  -5.000  -0.5533   0.01137   0.00454   0.0002   1.0000   0.0318
  -4.750  -0.5288   0.01101   0.00416   0.0008   1.0000   0.0333
  -4.500  -0.5045   0.01071   0.00384   0.0014   1.0000   0.0349
  -4.250  -0.4803   0.01045   0.00355   0.0021   1.0000   0.0361
  -4.000  -0.4560   0.01022   0.00328   0.0027   1.0000   0.0373
  -3.750  -0.4248   0.01000   0.00302   0.0019   0.9978   0.0385
  -3.500  -0.3880   0.00977   0.00278  -0.0002   0.9946   0.0405
  -3.250  -0.3532   0.00951   0.00254  -0.0018   0.9893   0.0462
  -3.000  -0.3189   0.00921   0.00238  -0.0034   0.9847   0.0687
  -2.750  -0.2872   0.00904   0.00227  -0.0043   0.9786   0.0859
  -2.500  -0.2553   0.00889   0.00215  -0.0052   0.9705   0.0949
  -2.250  -0.2255   0.00879   0.00206  -0.0056   0.9606   0.1030
  -2.000  -0.1981   0.00865   0.00196  -0.0054   0.9500   0.1126
  -1.750  -0.1716   0.00854   0.00186  -0.0050   0.9386   0.1193
  -1.500  -0.1457   0.00840   0.00176  -0.0045   0.9237   0.1302
  -1.250  -0.1199   0.00823   0.00166  -0.0039   0.9050   0.1494
  -1.000  -0.0961   0.00764   0.00145  -0.0032   0.8783   0.2706
  -0.750  -0.0740   0.00705   0.00129  -0.0021   0.8371   0.4333
  -0.500  -0.0499   0.00688   0.00120  -0.0012   0.7899   0.5057
  -0.250  -0.0246   0.00661   0.00116  -0.0007   0.7516   0.6024
   0.000   0.0000   0.00643   0.00116   0.0000   0.6973   0.6972
   0.250   0.0246   0.00661   0.00116   0.0007   0.6024   0.7517
   0.500   0.0500   0.00687   0.00120   0.0012   0.5069   0.7898
   0.750   0.0741   0.00705   0.00129   0.0021   0.4332   0.8372
   1.000   0.0961   0.00764   0.00145   0.0032   0.2691   0.8785
   1.250   0.1199   0.00823   0.00166   0.0039   0.1498   0.9051
   1.500   0.1457   0.00840   0.00176   0.0045   0.1304   0.9238
   1.750   0.1717   0.00854   0.00186   0.0050   0.1194   0.9387
   2.000   0.1982   0.00865   0.00196   0.0054   0.1126   0.9499
   2.250   0.2256   0.00879   0.00206   0.0056   0.1030   0.9606
   2.500   0.2553   0.00889   0.00215   0.0052   0.0949   0.9707
   2.750   0.2873   0.00904   0.00227   0.0043   0.0860   0.9788
   3.000   0.3190   0.00921   0.00238   0.0034   0.0689   0.9847
   3.250   0.3532   0.00951   0.00254   0.0018   0.0462   0.9893
   3.500   0.3880   0.00977   0.00278   0.0002   0.0405   0.9946
   3.750   0.4248   0.01000   0.00302  -0.0019   0.0385   0.9978
   4.000   0.4559   0.01022   0.00328  -0.0027   0.0373   1.0000
   4.250   0.4802   0.01045   0.00355  -0.0021   0.0361   1.0000
   4.500   0.5044   0.01071   0.00384  -0.0014   0.0349   1.0000
   4.750   0.5287   0.01101   0.00416  -0.0008   0.0333   1.0000
   5.000   0.5533   0.01137   0.00454  -0.0002   0.0318   1.0000
   5.250   0.5777   0.01187   0.00508   0.0003   0.0300   1.0000
   5.500   0.6022   0.01242   0.00569   0.0008   0.0287   1.0000
   5.750   0.6282   0.01269   0.00600   0.0011   0.0281   1.0000
   6.000   0.6542   0.01297   0.00633   0.0013   0.0271   1.0000
   6.250   0.6802   0.01331   0.00674   0.0015   0.0257   1.0000
   6.500   0.7062   0.01364   0.00712   0.0017   0.0240   1.0000
   6.750   0.7324   0.01395   0.00745   0.0019   0.0223   1.0000
   7.000   0.7578   0.01443   0.00795   0.0021   0.0206   1.0000
   7.250   0.7832   0.01493   0.00853   0.0023   0.0193   1.0000
   7.500   0.8095   0.01521   0.00889   0.0025   0.0178   1.0000
   7.750   0.8357   0.01552   0.00925   0.0026   0.0161   1.0000
   8.000   0.8617   0.01585   0.00958   0.0027   0.0147   1.0000
   8.250   0.8864   0.01648   0.01025   0.0030   0.0133   1.0000
   8.500   0.9112   0.01706   0.01094   0.0034   0.0123   1.0000
   8.750   0.9361   0.01759   0.01154   0.0036   0.0113   1.0000
   9.000   0.9608   0.01813   0.01213   0.0038   0.0104   1.0000
   9.250   0.9837   0.01907   0.01319   0.0043   0.0094   1.0000
   9.500   1.0065   0.02000   0.01427   0.0048   0.0090   1.0000
   9.750   1.0288   0.02099   0.01543   0.0054   0.0086   1.0000
  10.000   1.0504   0.02204   0.01665   0.0059   0.0082   1.0000
  10.250   1.0715   0.02313   0.01790   0.0065   0.0078   1.0000
  10.500   1.0921   0.02424   0.01916   0.0071   0.0074   1.0000
  10.750   1.1118   0.02541   0.02048   0.0078   0.0071   1.0000
  11.000   1.1285   0.02700   0.02225   0.0087   0.0067   1.0000
  11.250   1.1427   0.02892   0.02441   0.0097   0.0065   1.0000
  11.500   1.1568   0.03075   0.02652   0.0107   0.0063   1.0000
  11.750   1.1677   0.03292   0.02896   0.0119   0.0061   1.0000
  12.000   1.1742   0.03548   0.03180   0.0133   0.0059   1.0000
  12.250   1.1753   0.03849   0.03511   0.0148   0.0058   1.0000
  12.500   1.1682   0.04188   0.03878   0.0168   0.0057   1.0000
  12.750   1.1502   0.04601   0.04317   0.0185   0.0057   1.0000
  13.000   1.1226   0.05233   0.04977   0.0171   0.0057   1.0000
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