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NACA M25 AIRFOIL (m25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M25 AIRFOIL (m25-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.87 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m25-il-1000000.txt
Download as CSV file: xf-m25-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M25 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3555   0.10934   0.10665   0.0257   0.5779   0.0075
  -7.750  -0.3479   0.10638   0.10370   0.0236   0.5747   0.0076
  -7.500  -0.3411   0.10351   0.10083   0.0214   0.5712   0.0076
  -7.250  -0.3295   0.10040   0.09768   0.0181   0.5677   0.0076
  -7.000  -0.3158   0.09717   0.09442   0.0149   0.5640   0.0076
  -6.750  -0.3033   0.09320   0.09045   0.0120   0.5611   0.0077
  -6.500  -0.2918   0.08958   0.08682   0.0102   0.5576   0.0078
  -6.250  -0.2762   0.08653   0.08373   0.0076   0.5541   0.0080
  -6.000  -0.2587   0.08352   0.08069   0.0047   0.5506   0.0081
  -5.750  -0.2397   0.08048   0.07762   0.0018   0.5475   0.0084
  -5.500  -0.2194   0.07739   0.07450  -0.0013   0.5441   0.0087
  -5.250  -0.1978   0.07425   0.07132  -0.0044   0.5407   0.0092
  -5.000  -0.1733   0.07093   0.06793  -0.0077   0.5375   0.0102
  -4.750  -0.1424   0.06761   0.06453  -0.0121   0.5344   0.0104
  -4.500  -0.1130   0.06417   0.06103  -0.0160   0.5315   0.0105
  -4.250  -0.0938   0.06003   0.05686  -0.0179   0.5284   0.0108
  -4.000  -0.0705   0.05755   0.05433  -0.0199   0.5250   0.0111
  -3.750  -0.0445   0.05514   0.05184  -0.0220   0.5216   0.0117
  -3.500  -0.0166   0.05263   0.04926  -0.0243   0.5187   0.0131
  -3.250   0.0195   0.05007   0.04660  -0.0272   0.5157   0.0138
  -3.000   0.0528   0.04727   0.04369  -0.0296   0.5125   0.0139
  -2.750   0.0852   0.04435   0.04064  -0.0316   0.5095   0.0140
   2.250   0.2346   0.01459   0.01111   0.0320   0.4510   0.0303
   2.500   0.6912   0.01199   0.00586  -0.0399   0.4457   0.0326
   2.750   0.7193   0.01170   0.00556  -0.0402   0.4423   0.0344
   3.000   0.7476   0.01138   0.00518  -0.0404   0.4390   0.0371
   3.250   0.7762   0.01166   0.00541  -0.0406   0.4353   0.0404
   3.500   0.8039   0.01069   0.00437  -0.0408   0.4325   0.0448
   3.750   0.8321   0.01060   0.00429  -0.0411   0.4293   0.0498
   4.000   0.8600   0.01039   0.00409  -0.0414   0.4254   0.0583
   4.250   0.8870   0.00954   0.00306  -0.0407   0.4212   0.0339
   4.500   0.9147   0.00941   0.00292  -0.0408   0.4162   0.0319
   4.750   0.9422   0.00933   0.00279  -0.0409   0.4082   0.0320
   5.000   0.9698   0.00924   0.00271  -0.0411   0.4030   0.0341
   5.250   0.9976   0.00927   0.00273  -0.0414   0.3943   0.0358
   5.500   1.0255   0.00933   0.00278  -0.0417   0.3840   0.0369
   5.750   1.0532   0.00945   0.00287  -0.0421   0.3734   0.0384
   6.000   1.0807   0.00966   0.00301  -0.0425   0.3539   0.0399
   6.250   1.1070   0.01031   0.00340  -0.0431   0.3049   0.0419
   6.500   1.1187   0.01468   0.00638  -0.0445   0.0238   0.0745
   6.750   1.1520   0.01388   0.00718  -0.0466   0.0173   0.9926
   7.000   1.2172   0.01463   0.00797  -0.0559   0.0146   1.0000
   7.250   1.2396   0.01520   0.00860  -0.0556   0.0132   1.0000
   7.500   1.2598   0.01608   0.00957  -0.0552   0.0119   1.0000
   7.750   1.2768   0.01726   0.01089  -0.0545   0.0111   1.0000
   8.000   1.2967   0.01786   0.01152  -0.0539   0.0106   1.0000
   8.250   1.3148   0.01859   0.01229  -0.0532   0.0099   1.0000
   8.500   1.3295   0.01959   0.01335  -0.0523   0.0093   1.0000
   8.750   1.3403   0.02089   0.01475  -0.0514   0.0089   1.0000
   9.000   1.3452   0.02290   0.01685  -0.0511   0.0086   1.0000
   9.250   1.3405   0.02510   0.01911  -0.0492   0.0084   1.0000
   9.500   1.3398   0.02763   0.02172  -0.0485   0.0082   1.0000
   9.750   1.3386   0.03041   0.02458  -0.0481   0.0080   1.0000
  10.000   1.3343   0.03358   0.02782  -0.0477   0.0078   1.0000
  10.250   1.3258   0.03717   0.03150  -0.0472   0.0076   1.0000
  10.500   1.3136   0.04110   0.03551  -0.0464   0.0074   1.0000
  10.750   1.2992   0.04505   0.03954  -0.0453   0.0073   1.0000
  11.000   1.2912   0.04808   0.04262  -0.0437   0.0071   1.0000
  11.250   1.2979   0.05011   0.04471  -0.0435   0.0069   1.0000
  11.500   1.3023   0.05221   0.04688  -0.0428   0.0068   1.0000
  11.750   1.3081   0.05419   0.04891  -0.0421   0.0066   1.0000
  12.000   1.3142   0.05608   0.05085  -0.0413   0.0063   1.0000
  12.250   1.3213   0.05774   0.05256  -0.0403   0.0061   1.0000
  12.500   1.3308   0.05874   0.05359  -0.0383   0.0060   1.0000
  12.750   1.3443   0.05917   0.05404  -0.0358   0.0059   1.0000
  13.000   1.3603   0.05946   0.05439  -0.0332   0.0058   1.0000
  13.250   1.3766   0.06002   0.05502  -0.0307   0.0056   1.0000
  13.500   1.3904   0.06114   0.05622  -0.0287   0.0055   1.0000
  13.750   1.4605   0.06565   0.06108  -0.0191   0.0070   1.0000
  14.000   1.4513   0.06890   0.06449  -0.0186   0.0070   1.0000
  14.250   1.4407   0.07213   0.06787  -0.0184   0.0070   1.0000
  14.500   1.4287   0.07491   0.07080  -0.0187   0.0069   1.0000
  14.750   1.4192   0.07714   0.07316  -0.0195   0.0065   1.0000
  15.000   1.4086   0.08092   0.07710  -0.0200   0.0062   1.0000
  15.250   1.3979   0.08498   0.08131  -0.0206   0.0060   1.0000
  15.500   1.3868   0.08941   0.08589  -0.0214   0.0058   1.0000
  15.750   1.3754   0.09406   0.09068  -0.0226   0.0057   1.0000
  16.000   1.3634   0.09891   0.09567  -0.0239   0.0056   1.0000
  16.250   1.3508   0.10407   0.10095  -0.0256   0.0055   1.0000
  16.500   1.3378   0.10950   0.10652  -0.0275   0.0054   1.0000
  16.750   1.3242   0.11522   0.11237  -0.0298   0.0054   1.0000
  17.000   1.3105   0.12111   0.11839  -0.0324   0.0053   1.0000
  17.250   1.2965   0.12735   0.12476  -0.0353   0.0053   1.0000
  17.500   1.2818   0.13403   0.13156  -0.0386   0.0052   1.0000
  17.750   1.2675   0.14091   0.13857  -0.0422   0.0052   1.0000
  18.000   1.2528   0.14823   0.14601  -0.0463   0.0052   1.0000
  18.250   1.2373   0.15609   0.15399  -0.0509   0.0052   1.0000
  18.500   1.2217   0.16444   0.16246  -0.0559   0.0053   1.0000
  18.750   1.2052   0.17360   0.17175  -0.0615   0.0053   1.0000
  19.000   1.1884   0.18365   0.18192  -0.0679   0.0054   1.0000
  19.250   1.1715   0.19483   0.19321  -0.0749   0.0055   1.0000
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