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NACA M21 AIRFOIL (m21-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M21 AIRFOIL (m21-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.44 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m21-il-1000000-n5.txt
Download as CSV file: xf-m21-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3764   0.08367   0.08075  -0.0244   0.6094   0.0180
  -8.750  -0.3733   0.08074   0.07781  -0.0270   0.6047   0.0182
  -7.750  -0.4699   0.01926   0.01418  -0.0481   0.6002   0.0249
  -7.500  -0.4467   0.01756   0.01221  -0.0477   0.5959   0.0251
  -7.250  -0.4214   0.01653   0.01099  -0.0474   0.5911   0.0254
  -7.000  -0.3952   0.01576   0.01004  -0.0472   0.5859   0.0256
  -6.750  -0.3685   0.01513   0.00925  -0.0471   0.5812   0.0257
  -6.500  -0.3413   0.01459   0.00859  -0.0469   0.5764   0.0258
  -6.250  -0.3145   0.01393   0.00780  -0.0468   0.5717   0.0261
  -5.750  -0.2597   0.01296   0.00664  -0.0466   0.5626   0.0270
  -5.500  -0.2317   0.01266   0.00628  -0.0466   0.5577   0.0273
  -5.250  -0.2036   0.01237   0.00591  -0.0466   0.5531   0.0277
  -5.000  -0.1755   0.01208   0.00556  -0.0466   0.5490   0.0280
  -4.750  -0.1472   0.01180   0.00522  -0.0466   0.5445   0.0283
  -4.500  -0.1189   0.01155   0.00490  -0.0467   0.5397   0.0286
  -4.250  -0.0907   0.01131   0.00459  -0.0467   0.5353   0.0290
  -4.000  -0.0623   0.01108   0.00431  -0.0467   0.5315   0.0294
  -3.750  -0.0339   0.01086   0.00404  -0.0468   0.5270   0.0298
  -3.500  -0.0056   0.01067   0.00380  -0.0468   0.5224   0.0301
  -3.250   0.0228   0.01051   0.00358  -0.0469   0.5183   0.0305
  -3.000   0.0513   0.01035   0.00338  -0.0469   0.5145   0.0307
  -2.750   0.0795   0.01013   0.00313  -0.0469   0.5099   0.0316
  -2.500   0.1078   0.00999   0.00296  -0.0470   0.5055   0.0324
  -2.250   0.1362   0.00988   0.00283  -0.0471   0.5017   0.0332
  -2.000   0.1647   0.00977   0.00271  -0.0472   0.4978   0.0341
  -1.750   0.1932   0.00968   0.00259  -0.0473   0.4933   0.0351
  -1.500   0.2216   0.00960   0.00248  -0.0473   0.4890   0.0359
  -1.250   0.2499   0.00951   0.00237  -0.0474   0.4854   0.0370
  -1.000   0.2783   0.00942   0.00229  -0.0475   0.4814   0.0388
  -0.750   0.3068   0.00936   0.00223  -0.0476   0.4770   0.0405
  -0.500   0.3352   0.00933   0.00217  -0.0478   0.4727   0.0421
  -0.250   0.3636   0.00928   0.00212  -0.0479   0.4693   0.0442
   0.000   0.3922   0.00924   0.00210  -0.0480   0.4655   0.0467
   0.250   0.4207   0.00922   0.00207  -0.0482   0.4610   0.0490
   0.500   0.4490   0.00922   0.00205  -0.0484   0.4565   0.0510
   0.750   0.4775   0.00921   0.00206  -0.0485   0.4532   0.0540
   1.000   0.5061   0.00920   0.00206  -0.0487   0.4494   0.0564
   1.250   0.5346   0.00921   0.00206  -0.0489   0.4450   0.0582
   1.500   0.5628   0.00923   0.00206  -0.0491   0.4404   0.0598
   1.750   0.5912   0.00922   0.00208  -0.0493   0.4369   0.0627
   2.000   0.6197   0.00924   0.00211  -0.0495   0.4332   0.0657
   2.250   0.6481   0.00927   0.00214  -0.0497   0.4289   0.0681
   2.500   0.6763   0.00932   0.00218  -0.0499   0.4244   0.0694
   2.750   0.7045   0.00932   0.00219  -0.0501   0.4207   0.0723
   3.000   0.7327   0.00934   0.00223  -0.0503   0.4165   0.0750
   3.250   0.7609   0.00938   0.00228  -0.0505   0.4124   0.0775
   3.500   0.7888   0.00945   0.00234  -0.0507   0.4083   0.0799
   3.750   0.8171   0.00948   0.00239  -0.0509   0.4048   0.0819
   4.000   0.8451   0.00952   0.00245  -0.0511   0.4002   0.0857
   4.250   0.8729   0.00959   0.00253  -0.0513   0.3956   0.0897
   4.500   0.9007   0.00967   0.00261  -0.0515   0.3919   0.0936
   4.750   0.9287   0.00971   0.00270  -0.0517   0.3884   0.0998
   5.250   0.9813   0.00950   0.00301  -0.0517   0.3797   0.4066
   5.500   1.0017   0.00839   0.00327  -0.0503   0.3759   0.9712
   5.750   1.0356   0.00854   0.00344  -0.0519   0.3720   0.9827
   6.000   1.0780   0.00874   0.00363  -0.0554   0.3675   0.9875
   6.250   1.1136   0.00895   0.00381  -0.0575   0.3625   0.9906
   6.500   1.1469   0.00912   0.00399  -0.0590   0.3564   0.9936
   6.750   1.1810   0.00934   0.00417  -0.0608   0.3488   0.9946
   7.000   1.2169   0.00955   0.00436  -0.0630   0.3398   0.9959
   7.250   1.2544   0.00982   0.00459  -0.0657   0.3309   0.9978
   7.500   1.2908   0.01005   0.00481  -0.0681   0.3212   0.9993
   7.750   1.3212   0.01032   0.00505  -0.0692   0.3122   1.0000
   8.000   1.3429   0.01064   0.00532  -0.0684   0.3006   1.0000
   8.250   1.3637   0.01100   0.00562  -0.0675   0.2859   1.0000
   8.500   1.3841   0.01137   0.00594  -0.0665   0.2720   1.0000
   8.750   1.4028   0.01183   0.00632  -0.0653   0.2557   1.0000
   9.000   1.4182   0.01245   0.00682  -0.0636   0.2314   1.0000
   9.250   1.4230   0.01363   0.00773  -0.0603   0.1881   1.0000
   9.500   1.4207   0.01497   0.00881  -0.0558   0.1468   1.0000
   9.750   1.3937   0.01688   0.01042  -0.0472   0.0957   1.0000
  10.000   1.3655   0.01908   0.01244  -0.0398   0.0594   1.0000
  10.250   1.3490   0.02190   0.01510  -0.0361   0.0253   1.0000
  10.500   1.3545   0.02352   0.01672  -0.0349   0.0189   1.0000
  10.750   1.3635   0.02494   0.01818  -0.0340   0.0167   1.0000
  11.000   1.3721   0.02647   0.01974  -0.0332   0.0153   1.0000
  11.250   1.3804   0.02808   0.02139  -0.0325   0.0141   1.0000
  11.500   1.3890   0.02968   0.02304  -0.0319   0.0135   1.0000
  11.750   1.3964   0.03143   0.02484  -0.0314   0.0128   1.0000
  12.000   1.4022   0.03335   0.02681  -0.0308   0.0121   1.0000
  12.250   1.4064   0.03543   0.02894  -0.0302   0.0115   1.0000
  12.500   1.4097   0.03765   0.03121  -0.0296   0.0110   1.0000
  12.750   1.4145   0.03972   0.03334  -0.0291   0.0107   1.0000
  13.000   1.4180   0.04192   0.03560  -0.0286   0.0104   1.0000
  13.250   1.4209   0.04423   0.03797  -0.0282   0.0101   1.0000
  13.500   1.4233   0.04667   0.04048  -0.0279   0.0098   1.0000
  13.750   1.4249   0.04925   0.04311  -0.0276   0.0095   1.0000
  14.000   1.4259   0.05193   0.04585  -0.0274   0.0093   1.0000
  14.250   1.4263   0.05473   0.04871  -0.0272   0.0090   1.0000
  14.500   1.4257   0.05767   0.05171  -0.0271   0.0087   1.0000
  14.750   1.4232   0.06089   0.05499  -0.0270   0.0084   1.0000
  15.000   1.4232   0.06386   0.05803  -0.0270   0.0083   1.0000
  15.250   1.4240   0.06676   0.06100  -0.0271   0.0081   1.0000
  15.500   1.4237   0.06981   0.06411  -0.0272   0.0079   1.0000
  15.750   1.4228   0.07296   0.06733  -0.0274   0.0077   1.0000
  16.000   1.4223   0.07608   0.07052  -0.0276   0.0076   1.0000
  16.250   1.4204   0.07945   0.07395  -0.0279   0.0074   1.0000
  16.500   1.4188   0.08278   0.07735  -0.0282   0.0072   1.0000
  16.750   1.4170   0.08614   0.08078  -0.0286   0.0071   1.0000
  17.000   1.4141   0.08971   0.08441  -0.0290   0.0070   1.0000
  17.250   1.4122   0.09316   0.08792  -0.0295   0.0068   1.0000
  17.500   1.4086   0.09690   0.09173  -0.0301   0.0067   1.0000
  17.750   1.4052   0.10059   0.09549  -0.0308   0.0065   1.0000
  18.000   1.4007   0.10448   0.09944  -0.0315   0.0064   1.0000
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