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NACA M21 AIRFOIL (m21-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M21 AIRFOIL (m21-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.89 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m21-il-1000000.txt
Download as CSV file: xf-m21-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M21 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3031   0.09673   0.09401  -0.0159   0.6540   0.0226
  -8.500  -0.2966   0.09381   0.09108  -0.0176   0.6485   0.0232
  -8.250  -0.3040   0.08806   0.08533  -0.0250   0.6445   0.0251
  -8.000  -0.2139   0.07255   0.06985  -0.0320   0.6257   0.0257
  -7.750  -0.3041   0.07815   0.07537  -0.0329   0.6360   0.0254
  -7.500  -0.2924   0.07561   0.07280  -0.0337   0.6305   0.0256
  -7.250  -0.2791   0.07328   0.07042  -0.0348   0.6253   0.0258
  -7.000  -0.2649   0.07083   0.06795  -0.0363   0.6206   0.0261
  -6.750  -0.2498   0.06828   0.06536  -0.0381   0.6157   0.0265
  -6.500  -0.2338   0.06560   0.06260  -0.0400   0.6107   0.0271
  -5.500  -0.2222   0.01875   0.01369  -0.0475   0.6014   0.0305
  -5.250  -0.1983   0.01714   0.01181  -0.0471   0.5964   0.0309
  -5.000  -0.1725   0.01613   0.01062  -0.0468   0.5917   0.0313
  -4.750  -0.1460   0.01521   0.00954  -0.0467   0.5872   0.0317
  -4.500  -0.1191   0.01441   0.00856  -0.0465   0.5822   0.0322
  -4.250  -0.0919   0.01375   0.00773  -0.0464   0.5771   0.0328
  -4.000  -0.0641   0.01313   0.00700  -0.0463   0.5730   0.0334
  -3.750  -0.0361   0.01263   0.00637  -0.0463   0.5684   0.0339
  -3.500  -0.0079   0.01228   0.00592  -0.0463   0.5635   0.0344
  -3.250   0.0203   0.01193   0.00546  -0.0463   0.5590   0.0349
  -3.000   0.0478   0.01117   0.00461  -0.0463   0.5548   0.0359
  -2.750   0.0762   0.01093   0.00434  -0.0463   0.5502   0.0366
  -2.500   0.1045   0.01078   0.00413  -0.0464   0.5453   0.0374
  -2.250   0.1331   0.01058   0.00391  -0.0465   0.5414   0.0383
  -2.000   0.1616   0.01038   0.00368  -0.0465   0.5371   0.0393
  -1.750   0.1900   0.01024   0.00348  -0.0466   0.5326   0.0401
  -1.500   0.2177   0.00997   0.00314  -0.0465   0.5279   0.0414
  -1.250   0.2461   0.00980   0.00300  -0.0466   0.5243   0.0430
  -1.000   0.2748   0.00975   0.00296  -0.0468   0.5200   0.0446
  -0.750   0.3034   0.00970   0.00287  -0.0469   0.5156   0.0463
  -0.500   0.3313   0.00957   0.00270  -0.0469   0.5112   0.0482
  -0.250   0.3599   0.00947   0.00264  -0.0470   0.5074   0.0506
   0.000   0.3886   0.00946   0.00262  -0.0472   0.5033   0.0529
   0.250   0.4173   0.00948   0.00261  -0.0474   0.4989   0.0548
   0.500   0.4451   0.00936   0.00250  -0.0474   0.4948   0.0581
   0.750   0.4741   0.00937   0.00253  -0.0476   0.4908   0.0608
   1.000   0.5028   0.00939   0.00254  -0.0478   0.4866   0.0632
   1.250   0.5309   0.00938   0.00250  -0.0480   0.4824   0.0651
   1.500   0.5589   0.00929   0.00243  -0.0481   0.4785   0.0686
   1.750   0.5875   0.00929   0.00246  -0.0483   0.4745   0.0714
   2.000   0.6160   0.00930   0.00246  -0.0485   0.4700   0.0739
   2.250   0.6443   0.00938   0.00251  -0.0487   0.4656   0.0754
   2.500   0.6719   0.00924   0.00240  -0.0487   0.4621   0.0798
   2.750   0.7003   0.00924   0.00242  -0.0489   0.4581   0.0830
   3.000   0.7285   0.00926   0.00243  -0.0491   0.4536   0.0859
   3.250   0.7563   0.00934   0.00248  -0.0493   0.4488   0.0878
   3.500   0.7845   0.00927   0.00245  -0.0494   0.4455   0.0929
   3.750   0.8126   0.00928   0.00249  -0.0496   0.4414   0.0973
   4.000   0.8406   0.00933   0.00253  -0.0498   0.4370   0.1009
   4.250   0.8682   0.00939   0.00260  -0.0499   0.4325   0.1087
   4.500   0.8964   0.00938   0.00265  -0.0502   0.4286   0.1241
   4.750   0.9150   0.00779   0.00299  -0.0485   0.4248   0.9713
   5.000   0.9792   0.00814   0.00330  -0.0568   0.4190   0.9900
   5.250   1.0369   0.00834   0.00349  -0.0636   0.4142   0.9955
   5.500   1.0868   0.00847   0.00361  -0.0687   0.4088   0.9985
   5.750   1.1256   0.00863   0.00373  -0.0715   0.4037   1.0000
   6.000   1.1510   0.00874   0.00384  -0.0712   0.3999   1.0000
   6.250   1.1763   0.00883   0.00394  -0.0710   0.3941   1.0000
   6.500   1.2008   0.00901   0.00408  -0.0706   0.3873   1.0000
   6.750   1.2259   0.00910   0.00420  -0.0703   0.3822   1.0000
   7.000   1.2504   0.00925   0.00433  -0.0699   0.3754   1.0000
   7.250   1.2746   0.00943   0.00450  -0.0695   0.3696   1.0000
   7.500   1.2991   0.00956   0.00464  -0.0691   0.3636   1.0000
   7.750   1.3222   0.00980   0.00485  -0.0686   0.3557   1.0000
   8.000   1.3463   0.00994   0.00501  -0.0682   0.3480   1.0000
   8.250   1.3689   0.01020   0.00524  -0.0675   0.3402   1.0000
   8.500   1.3923   0.01038   0.00543  -0.0670   0.3324   1.0000
   8.750   1.4141   0.01067   0.00569  -0.0662   0.3215   1.0000
   9.000   1.4348   0.01101   0.00598  -0.0653   0.3092   1.0000
   9.250   1.4544   0.01141   0.00632  -0.0642   0.2929   1.0000
   9.500   1.4710   0.01197   0.00677  -0.0627   0.2695   1.0000
   9.750   1.4779   0.01304   0.00758  -0.0597   0.2264   1.0000
  10.000   1.4659   0.01489   0.00901  -0.0538   0.1646   1.0000
  10.250   1.4428   0.01662   0.01047  -0.0459   0.1208   1.0000
  10.500   1.4144   0.01892   0.01257  -0.0386   0.0827   1.0000
  10.750   1.3899   0.02239   0.01582  -0.0344   0.0409   1.0000
  11.000   1.3839   0.02502   0.01839  -0.0326   0.0247   1.0000
  11.250   1.3887   0.02689   0.02029  -0.0317   0.0211   1.0000
  11.500   1.3928   0.02889   0.02233  -0.0308   0.0192   1.0000
  11.750   1.3981   0.03082   0.02432  -0.0301   0.0180   1.0000
  12.000   1.4039   0.03274   0.02630  -0.0295   0.0173   1.0000
  12.250   1.4075   0.03489   0.02850  -0.0289   0.0166   1.0000
  12.500   1.4090   0.03727   0.03094  -0.0282   0.0159   1.0000
  12.750   1.4071   0.04002   0.03377  -0.0276   0.0152   1.0000
  13.000   1.4061   0.04270   0.03652  -0.0270   0.0149   1.0000
  13.250   1.4083   0.04513   0.03901  -0.0266   0.0146   1.0000
  13.500   1.4094   0.04773   0.04170  -0.0262   0.0142   1.0000
  13.750   1.4093   0.05052   0.04456  -0.0260   0.0139   1.0000
  14.000   1.4088   0.05343   0.04753  -0.0258   0.0136   1.0000
  14.250   1.4078   0.05643   0.05060  -0.0256   0.0132   1.0000
  14.500   1.4058   0.05957   0.05380  -0.0256   0.0129   1.0000
  14.750   1.4017   0.06302   0.05732  -0.0255   0.0126   1.0000
  15.000   1.3945   0.06693   0.06131  -0.0256   0.0123   1.0000
  15.250   1.3827   0.07148   0.06596  -0.0258   0.0120   1.0000
  15.500   1.3803   0.07489   0.06945  -0.0260   0.0119   1.0000
  15.750   1.3795   0.07813   0.07276  -0.0263   0.0117   1.0000
  16.000   1.3777   0.08154   0.07624  -0.0266   0.0116   1.0000
  16.250   1.3746   0.08513   0.07991  -0.0270   0.0114   1.0000
  16.500   1.3722   0.08863   0.08348  -0.0274   0.0112   1.0000
  16.750   1.3689   0.09234   0.08726  -0.0279   0.0110   1.0000
  17.000   1.3658   0.09604   0.09102  -0.0285   0.0108   1.0000
  17.250   1.3627   0.09973   0.09478  -0.0291   0.0107   1.0000
  17.500   1.3593   0.10349   0.09861  -0.0298   0.0105   1.0000
  17.750   1.3568   0.10714   0.10232  -0.0306   0.0103   1.0000
  18.000   1.3532   0.11102   0.10626  -0.0314   0.0102   1.0000
  18.250   1.3504   0.11476   0.11005  -0.0323   0.0100   1.0000
  18.500   1.3456   0.11884   0.11419  -0.0333   0.0098   1.0000
  18.750   1.3405   0.12287   0.11828  -0.0344   0.0097   1.0000
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