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NACA M7 AIRFOIL (m7-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M7 AIRFOIL (m7-il)
Reynolds number: 100,000
Max Cl/Cd: 54.08 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m7-il-100000-n5.txt
Download as CSV file: xf-m7-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M7 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4499   0.10132   0.09734   0.0217   0.8492   0.0211
  -7.000  -0.4444   0.09837   0.09434   0.0200   0.8343   0.0216
  -6.750  -0.4360   0.09522   0.09114   0.0178   0.8217   0.0221
  -6.500  -0.4260   0.09201   0.08787   0.0156   0.8104   0.0227
  -6.250  -0.4138   0.08872   0.08450   0.0130   0.7993   0.0234
  -6.000  -0.4000   0.08544   0.08115   0.0104   0.7894   0.0242
  -5.750  -0.3844   0.08223   0.07785   0.0077   0.7805   0.0251
  -5.500  -0.3640   0.07919   0.07472   0.0041   0.7708   0.0261
  -5.250  -0.3382   0.07678   0.07213  -0.0002   0.7622   0.0268
  -5.000  -0.3111   0.07438   0.06954  -0.0039   0.7536   0.0271
  -4.750  -0.2940   0.07016   0.06527  -0.0051   0.7457   0.0275
  -4.500  -0.2874   0.06556   0.06069  -0.0038   0.7384   0.0293
  -4.250  -0.2668   0.06252   0.05754  -0.0051   0.7301   0.0321
  -4.000  -0.2255   0.06183   0.05644  -0.0091   0.7229   0.0363
  -3.500  -0.1941   0.05374   0.04827  -0.0093   0.7085   0.0403
  -3.250  -0.1626   0.05189   0.04618  -0.0109   0.7006   0.0458
  -3.000  -0.1303   0.04982   0.04377  -0.0120   0.6942   0.0481
  -2.750  -0.1146   0.04578   0.03975  -0.0120   0.6869   0.0509
  -2.500  -0.0895   0.04345   0.03721  -0.0122   0.6803   0.0563
  -2.250  -0.0565   0.04164   0.03503  -0.0129   0.6735   0.0625
  -2.000  -0.0354   0.03872   0.03205  -0.0128   0.6668   0.0671
  -1.750  -0.0004   0.03798   0.03079  -0.0128   0.6605   0.0756
  -1.500   0.0230   0.03471   0.02745  -0.0128   0.6536   0.0773
  -1.250   0.0499   0.03255   0.02503  -0.0124   0.6482   0.0788
  -1.000   0.0865   0.02931   0.02130  -0.0113   0.6416   0.0337
  -0.750   0.1157   0.02720   0.01885  -0.0107   0.6358   0.0307
  -0.500   0.1471   0.02519   0.01636  -0.0100   0.6296   0.0284
  -0.250   0.1772   0.02379   0.01455  -0.0093   0.6232   0.0269
   0.000   0.2058   0.02221   0.01266  -0.0089   0.6179   0.0259
   0.250   0.2356   0.02086   0.01105  -0.0086   0.6108   0.0253
   0.500   0.2644   0.01969   0.00959  -0.0081   0.6054   0.0252
   0.750   0.2936   0.01874   0.00847  -0.0079   0.5987   0.0257
   1.000   0.3221   0.01793   0.00754  -0.0076   0.5927   0.0288
   1.250   0.3513   0.01742   0.00685  -0.0075   0.5867   0.0314
   1.500   0.3789   0.01713   0.00638  -0.0072   0.5801   0.0354
   1.750   0.4052   0.01687   0.00603  -0.0065   0.5751   0.0563
   2.250   0.5109   0.01512   0.00593  -0.0171   0.5608   1.0000
   2.500   0.5374   0.01529   0.00599  -0.0170   0.5538   1.0000
   2.750   0.5632   0.01544   0.00600  -0.0166   0.5480   1.0000
   3.000   0.5892   0.01561   0.00608  -0.0163   0.5420   1.0000
   3.250   0.6152   0.01579   0.00621  -0.0161   0.5355   1.0000
   3.500   0.6407   0.01589   0.00624  -0.0156   0.5271   1.0000
   3.750   0.6657   0.01590   0.00613  -0.0150   0.5162   1.0000
   4.000   0.6912   0.01593   0.00611  -0.0145   0.5024   1.0000
   4.250   0.7169   0.01602   0.00623  -0.0143   0.4903   1.0000
   4.500   0.7426   0.01620   0.00641  -0.0140   0.4826   1.0000
   4.750   0.7683   0.01638   0.00662  -0.0137   0.4749   1.0000
   5.000   0.7940   0.01658   0.00692  -0.0135   0.4672   1.0000
   5.250   0.8195   0.01677   0.00716  -0.0132   0.4593   1.0000
   5.500   0.8450   0.01693   0.00740  -0.0129   0.4471   1.0000
   5.750   0.8704   0.01708   0.00762  -0.0126   0.4334   1.0000
   6.000   0.8957   0.01729   0.00797  -0.0123   0.4225   1.0000
   6.250   0.9210   0.01750   0.00829  -0.0121   0.4096   1.0000
   6.500   0.9459   0.01771   0.00859  -0.0118   0.3889   1.0000
   6.750   0.9705   0.01799   0.00897  -0.0115   0.3630   1.0000
   7.000   0.9946   0.01839   0.00939  -0.0113   0.3284   1.0000
   7.250   1.0171   0.01911   0.00995  -0.0111   0.2714   1.0000
   7.500   1.0316   0.02144   0.01145  -0.0114   0.1403   1.0000
   7.750   1.0453   0.02370   0.01330  -0.0114   0.0823   1.0000
   8.000   1.0638   0.02488   0.01457  -0.0109   0.0736   1.0000
   8.250   1.0809   0.02613   0.01596  -0.0104   0.0695   1.0000
   8.500   1.0978   0.02730   0.01733  -0.0098   0.0672   1.0000
   8.750   1.1133   0.02851   0.01877  -0.0092   0.0653   1.0000
   9.000   1.1268   0.02984   0.02033  -0.0084   0.0636   1.0000
   9.250   1.1381   0.03129   0.02204  -0.0075   0.0621   1.0000
   9.500   1.1472   0.03285   0.02380  -0.0065   0.0607   1.0000
   9.750   1.1540   0.03456   0.02569  -0.0055   0.0595   1.0000
  10.000   1.1580   0.03634   0.02761  -0.0041   0.0584   1.0000
  10.250   1.1607   0.03834   0.02966  -0.0028   0.0558   1.0000
  10.500   1.1662   0.04025   0.03180  -0.0026   0.0497   1.0000
  10.750   1.1656   0.04281   0.03437  -0.0026   0.0437   1.0000
  11.000   1.1703   0.04500   0.03680  -0.0024   0.0390   1.0000
  11.250   1.1701   0.04774   0.03964  -0.0025   0.0341   1.0000
  11.500   1.1734   0.05031   0.04254  -0.0026   0.0273   1.0000
  11.750   1.1725   0.05337   0.04574  -0.0029   0.0223   1.0000
  12.000   1.1757   0.05591   0.04848  -0.0020   0.0178   1.0000
  12.250   1.1771   0.05879   0.05159  -0.0024   0.0149   1.0000
  12.500   1.1757   0.06207   0.05498  -0.0032   0.0133   1.0000
  12.750   1.1711   0.06573   0.05870  -0.0033   0.0123   1.0000
  13.000   1.1694   0.06909   0.06227  -0.0028   0.0117   1.0000
  13.250   1.1666   0.07276   0.06616  -0.0026   0.0112   1.0000
  13.500   1.1619   0.07684   0.07047  -0.0029   0.0108   1.0000
  13.750   1.1551   0.08135   0.07520  -0.0036   0.0106   1.0000
  14.000   1.1465   0.08633   0.08042  -0.0049   0.0103   1.0000
  14.250   1.1363   0.09180   0.08611  -0.0067   0.0102   1.0000
  14.500   1.1243   0.09780   0.09232  -0.0091   0.0101   1.0000
  14.750   1.1109   0.10439   0.09911  -0.0120   0.0101   1.0000
  15.000   1.0957   0.11164   0.10657  -0.0155   0.0101   1.0000
  15.250   1.0789   0.11964   0.11476  -0.0197   0.0103   1.0000
  15.500   1.0613   0.12840   0.12367  -0.0244   0.0105   1.0000
  15.750   1.0436   0.13777   0.13317  -0.0297   0.0108   1.0000
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