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NACA M3 AIRFOIL (m3-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M3 AIRFOIL (m3-il)
Reynolds number: 200,000
Max Cl/Cd: 45.8 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m3-il-200000.txt
Download as CSV file: xf-m3-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M3 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6450   0.09044   0.08670  -0.0275   1.0000   0.0592
 -12.250  -0.9128   0.06896   0.06448  -0.0375   1.0000   0.0504
 -12.000  -0.9334   0.06401   0.05939  -0.0377   1.0000   0.0500
 -11.750  -0.9548   0.05973   0.05493  -0.0365   1.0000   0.0497
 -11.500  -0.9752   0.05600   0.05099  -0.0337   1.0000   0.0493
 -11.250  -0.9915   0.05233   0.04706  -0.0305   1.0000   0.0490
 -11.000  -1.0018   0.04859   0.04300  -0.0276   1.0000   0.0488
 -10.750  -1.0065   0.04513   0.03919  -0.0248   1.0000   0.0489
 -10.500  -1.0058   0.04220   0.03589  -0.0221   1.0000   0.0494
 -10.250  -1.0005   0.03971   0.03301  -0.0196   1.0000   0.0500
 -10.000  -0.9918   0.03758   0.03051  -0.0173   1.0000   0.0506
  -9.750  -0.9801   0.03576   0.02834  -0.0151   1.0000   0.0510
  -9.500  -0.9652   0.03246   0.02480  -0.0139   1.0000   0.0517
  -9.250  -0.9459   0.03049   0.02278  -0.0130   1.0000   0.0530
  -9.000  -0.9266   0.02922   0.02142  -0.0119   1.0000   0.0543
  -8.750  -0.9067   0.02796   0.02004  -0.0108   1.0000   0.0556
  -8.500  -0.8863   0.02663   0.01857  -0.0096   1.0000   0.0567
  -8.250  -0.8656   0.02541   0.01720  -0.0084   1.0000   0.0579
  -8.000  -0.8450   0.02445   0.01608  -0.0071   1.0000   0.0593
  -7.750  -0.8243   0.02337   0.01488  -0.0058   1.0000   0.0606
  -7.500  -0.8036   0.02196   0.01351  -0.0048   1.0000   0.0624
  -7.250  -0.7836   0.02106   0.01264  -0.0034   1.0000   0.0641
  -7.000  -0.7640   0.02028   0.01183  -0.0020   1.0000   0.0661
  -6.750  -0.7446   0.01958   0.01109  -0.0004   1.0000   0.0685
  -6.500  -0.7255   0.01895   0.01040   0.0012   1.0000   0.0710
  -6.250  -0.7094   0.01799   0.00953   0.0032   1.0000   0.0745
  -6.000  -0.6915   0.01737   0.00891   0.0050   1.0000   0.0786
  -5.750  -0.6741   0.01671   0.00824   0.0069   1.0000   0.0838
  -5.500  -0.6572   0.01603   0.00762   0.0087   1.0000   0.0930
  -5.250  -0.6411   0.01518   0.00696   0.0107   1.0000   0.1142
  -5.000  -0.6254   0.01422   0.00636   0.0126   1.0000   0.1688
  -4.750  -0.6082   0.01346   0.00597   0.0141   1.0000   0.2341
  -4.500  -0.5896   0.01291   0.00571   0.0154   1.0000   0.2953
  -4.250  -0.5700   0.01244   0.00551   0.0166   1.0000   0.3544
  -4.000  -0.5498   0.01203   0.00536   0.0178   1.0000   0.4138
  -3.750  -0.5290   0.01171   0.00528   0.0188   1.0000   0.4705
  -3.500  -0.5079   0.01143   0.00524   0.0199   1.0000   0.5257
  -3.250  -0.4866   0.01122   0.00526   0.0210   1.0000   0.5821
  -3.000  -0.4652   0.01108   0.00536   0.0222   1.0000   0.6354
  -2.750  -0.4437   0.01102   0.00548   0.0234   1.0000   0.6820
  -2.500  -0.4075   0.01101   0.00561   0.0218   0.9959   0.7253
  -2.250  -0.3683   0.01104   0.00573   0.0196   0.9903   0.7621
  -2.000  -0.3289   0.01112   0.00590   0.0175   0.9844   0.7960
  -1.750  -0.2918   0.01119   0.00603   0.0160   0.9775   0.8239
  -1.500  -0.2516   0.01129   0.00616   0.0139   0.9714   0.8466
  -1.250  -0.2154   0.01139   0.00628   0.0127   0.9637   0.8670
  -1.000  -0.1737   0.01150   0.00639   0.0104   0.9578   0.8848
  -0.750  -0.1329   0.01160   0.00649   0.0083   0.9510   0.8994
  -0.500  -0.0891   0.01166   0.00654   0.0056   0.9444   0.9117
  -0.250  -0.0411   0.01167   0.00654   0.0021   0.9398   0.9217
   0.000   0.0000   0.01172   0.00659   0.0000   0.9298   0.9298
   0.250   0.0411   0.01167   0.00654  -0.0021   0.9217   0.9398
   0.500   0.0891   0.01166   0.00654  -0.0056   0.9117   0.9444
   0.750   0.1329   0.01160   0.00649  -0.0083   0.8994   0.9510
   1.000   0.1737   0.01150   0.00639  -0.0104   0.8848   0.9578
   1.250   0.2154   0.01139   0.00628  -0.0127   0.8670   0.9637
   1.500   0.2516   0.01129   0.00616  -0.0139   0.8466   0.9715
   1.750   0.2919   0.01119   0.00603  -0.0160   0.8240   0.9775
   2.000   0.3289   0.01111   0.00590  -0.0175   0.7960   0.9845
   2.250   0.3683   0.01104   0.00573  -0.0196   0.7621   0.9903
   2.500   0.4075   0.01101   0.00560  -0.0218   0.7252   0.9959
   2.750   0.4435   0.01102   0.00548  -0.0234   0.6820   1.0000
   3.000   0.4651   0.01107   0.00535  -0.0222   0.6354   1.0000
   3.250   0.4865   0.01122   0.00526  -0.0210   0.5821   1.0000
   3.500   0.5078   0.01143   0.00524  -0.0199   0.5259   1.0000
   3.750   0.5288   0.01171   0.00527  -0.0188   0.4706   1.0000
   4.000   0.5497   0.01203   0.00536  -0.0177   0.4137   1.0000
   4.250   0.5698   0.01244   0.00550  -0.0166   0.3546   1.0000
   4.500   0.5895   0.01290   0.00570  -0.0154   0.2954   1.0000
   4.750   0.6081   0.01346   0.00597  -0.0141   0.2343   1.0000
   5.000   0.6253   0.01421   0.00635  -0.0125   0.1690   1.0000
   5.250   0.6410   0.01517   0.00695  -0.0107   0.1143   1.0000
   5.500   0.6571   0.01602   0.00762  -0.0087   0.0931   1.0000
   5.750   0.6740   0.01671   0.00824  -0.0069   0.0839   1.0000
   6.000   0.6914   0.01737   0.00891  -0.0049   0.0786   1.0000
   6.250   0.7093   0.01798   0.00952  -0.0032   0.0745   1.0000
   6.500   0.7254   0.01895   0.01040  -0.0012   0.0710   1.0000
   6.750   0.7446   0.01958   0.01109   0.0004   0.0685   1.0000
   7.000   0.7639   0.02027   0.01183   0.0020   0.0661   1.0000
   7.250   0.7836   0.02106   0.01263   0.0034   0.0641   1.0000
   7.500   0.8035   0.02195   0.01351   0.0048   0.0624   1.0000
   7.750   0.8242   0.02336   0.01487   0.0058   0.0606   1.0000
   8.000   0.8450   0.02444   0.01607   0.0071   0.0593   1.0000
   8.250   0.8656   0.02541   0.01720   0.0084   0.0579   1.0000
   8.500   0.8863   0.02663   0.01857   0.0096   0.0567   1.0000
   8.750   0.9067   0.02795   0.02004   0.0108   0.0556   1.0000
   9.000   0.9267   0.02923   0.02143   0.0119   0.0543   1.0000
   9.250   0.9460   0.03049   0.02278   0.0130   0.0529   1.0000
   9.500   0.9653   0.03247   0.02481   0.0138   0.0517   1.0000
   9.750   0.9802   0.03577   0.02834   0.0151   0.0510   1.0000
  10.000   0.9920   0.03759   0.03051   0.0172   0.0506   1.0000
  10.250   1.0007   0.03970   0.03301   0.0196   0.0500   1.0000
  10.500   1.0059   0.04220   0.03589   0.0221   0.0493   1.0000
  10.750   1.0067   0.04514   0.03920   0.0248   0.0488   1.0000
  11.000   1.0020   0.04861   0.04302   0.0276   0.0488   1.0000
  11.250   0.9918   0.05235   0.04709   0.0305   0.0490   1.0000
  11.500   0.9755   0.05603   0.05103   0.0336   0.0493   1.0000
  11.750   0.9550   0.05978   0.05498   0.0364   0.0497   1.0000
  12.000   0.9337   0.06407   0.05945   0.0376   0.0500   1.0000
  12.250   0.9131   0.06903   0.06456   0.0373   0.0504   1.0000
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