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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 100,000
Max Cl/Cd: 38.73 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212ma-il-100000-n5.txt
Download as CSV file: xf-n64212ma-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3817   0.10958   0.10421  -0.0258   1.0000   0.0601
 -10.000  -0.3835   0.10596   0.10063  -0.0285   1.0000   0.0626
  -9.750  -0.3991   0.10130   0.09605  -0.0345   1.0000   0.0636
  -9.500  -0.3898   0.09779   0.09259  -0.0341   1.0000   0.0641
  -9.250  -0.3792   0.09490   0.08973  -0.0334   1.0000   0.0652
  -9.000  -0.3754   0.09167   0.08655  -0.0343   1.0000   0.0663
  -8.750  -0.3757   0.08812   0.08307  -0.0360   1.0000   0.0676
  -8.500  -0.3815   0.08409   0.07911  -0.0389   1.0000   0.0689
  -8.250  -0.4014   0.07945   0.07455  -0.0432   1.0000   0.0699
  -8.000  -0.4273   0.07648   0.07162  -0.0438   1.0000   0.0704
  -7.750  -0.4566   0.07437   0.06949  -0.0421   1.0000   0.0708
  -7.500  -0.4573   0.07014   0.06507  -0.0452   0.9889   0.0713
  -7.250  -0.4323   0.06615   0.06118  -0.0470   0.9824   0.0724
  -7.000  -0.4112   0.06242   0.05738  -0.0501   0.9729   0.0742
  -6.750  -0.3965   0.05829   0.05274  -0.0554   0.9601   0.0800
  -6.250  -0.3501   0.04671   0.04038  -0.0592   0.9418   0.0503
  -6.000  -0.3235   0.04357   0.03703  -0.0610   0.9347   0.0490
  -5.750  -0.3026   0.04067   0.03382  -0.0612   0.9238   0.0478
  -5.500  -0.2762   0.03761   0.03034  -0.0620   0.9166   0.0467
  -5.250  -0.2542   0.03580   0.02832  -0.0618   0.9063   0.0478
  -5.000  -0.2272   0.03380   0.02601  -0.0621   0.8982   0.0488
  -4.750  -0.2037   0.03196   0.02388  -0.0615   0.8874   0.0489
  -4.500  -0.1765   0.03011   0.02172  -0.0613   0.8782   0.0487
  -4.250  -0.1519   0.02857   0.01992  -0.0605   0.8671   0.0486
  -4.000  -0.1250   0.02711   0.01820  -0.0600   0.8574   0.0488
  -3.750  -0.0995   0.02586   0.01672  -0.0592   0.8466   0.0491
  -3.500  -0.0730   0.02477   0.01536  -0.0584   0.8363   0.0503
  -3.250  -0.0470   0.02380   0.01428  -0.0578   0.8266   0.0517
  -3.000  -0.0212   0.02293   0.01336  -0.0571   0.8162   0.0528
  -2.750   0.0060   0.02204   0.01238  -0.0564   0.8080   0.0534
  -2.500   0.0315   0.02129   0.01159  -0.0556   0.7978   0.0542
  -2.250   0.0581   0.02056   0.01081  -0.0549   0.7902   0.0552
  -2.000   0.0841   0.01995   0.01015  -0.0541   0.7824   0.0564
  -1.750   0.1088   0.01936   0.00964  -0.0533   0.7723   0.0585
  -1.500   0.1341   0.01882   0.00912  -0.0524   0.7631   0.0611
  -1.250   0.1578   0.01838   0.00868  -0.0513   0.7506   0.0631
  -1.000   0.1823   0.01787   0.00817  -0.0502   0.7398   0.0651
  -0.750   0.2063   0.01748   0.00776  -0.0493   0.7256   0.0677
  -0.500   0.2316   0.01714   0.00734  -0.0484   0.7122   0.0721
  -0.250   0.2572   0.01681   0.00695  -0.0477   0.6990   0.0785
   0.000   0.2828   0.01651   0.00664  -0.0471   0.6848   0.0863
   0.250   0.3089   0.01615   0.00632  -0.0465   0.6715   0.1066
   0.500   0.3233   0.01429   0.00641  -0.0442   0.6581   0.6563
   0.750   0.3414   0.01427   0.00665  -0.0409   0.6436   0.7494
   1.000   0.3599   0.01433   0.00675  -0.0378   0.6264   0.7990
   1.250   0.3769   0.01439   0.00683  -0.0344   0.6078   0.8379
   1.500   0.3931   0.01444   0.00686  -0.0308   0.5857   0.8725
   1.750   0.4134   0.01446   0.00677  -0.0285   0.5518   0.8940
   2.000   0.4367   0.01454   0.00662  -0.0272   0.5033   0.9069
   2.250   0.4570   0.01494   0.00643  -0.0256   0.3924   0.9194
   2.500   0.4772   0.01569   0.00660  -0.0246   0.3022   0.9328
   2.750   0.5033   0.01629   0.00687  -0.0248   0.2574   0.9465
   3.000   0.5343   0.01678   0.00714  -0.0258   0.2298   0.9605
   3.250   0.5685   0.01720   0.00742  -0.0276   0.2095   0.9754
   3.500   0.6027   0.01763   0.00770  -0.0294   0.1946   0.9975
   3.750   0.6226   0.01799   0.00797  -0.0285   0.1854   1.0000
   4.000   0.6437   0.01840   0.00827  -0.0277   0.1782   1.0000
   4.250   0.6664   0.01879   0.00860  -0.0272   0.1720   1.0000
   4.750   0.7126   0.01966   0.00932  -0.0261   0.1633   1.0000
   5.000   0.7361   0.02009   0.00971  -0.0257   0.1599   1.0000
   5.250   0.7594   0.02056   0.01011  -0.0252   0.1572   1.0000
   5.750   0.8065   0.02153   0.01101  -0.0242   0.1533   1.0000
   6.000   0.8304   0.02202   0.01150  -0.0238   0.1516   1.0000
   6.250   0.8543   0.02252   0.01199  -0.0234   0.1499   1.0000
   6.500   0.8779   0.02303   0.01248  -0.0230   0.1477   1.0000
   6.750   0.9009   0.02355   0.01297  -0.0225   0.1453   1.0000
   7.000   0.9242   0.02405   0.01349  -0.0220   0.1425   1.0000
   7.250   0.9473   0.02455   0.01402  -0.0216   0.1395   1.0000
   7.500   0.9696   0.02506   0.01455  -0.0210   0.1368   1.0000
   7.750   0.9915   0.02562   0.01508  -0.0205   0.1347   1.0000
   8.000   1.0143   0.02619   0.01574  -0.0200   0.1326   1.0000
   8.250   1.0362   0.02676   0.01637  -0.0194   0.1304   1.0000
   8.500   1.0571   0.02734   0.01699  -0.0187   0.1282   1.0000
   8.750   1.0775   0.02797   0.01761  -0.0180   0.1264   1.0000
   9.000   1.0985   0.02861   0.01838  -0.0174   0.1242   1.0000
   9.250   1.1178   0.02925   0.01909  -0.0166   0.1217   1.0000
   9.500   1.1348   0.02991   0.01974  -0.0155   0.1192   1.0000
   9.750   1.1517   0.03061   0.02057  -0.0144   0.1162   1.0000
  10.000   1.1669   0.03134   0.02134  -0.0131   0.1135   1.0000
  10.250   1.1820   0.03217   0.02220  -0.0119   0.1108   1.0000
  10.500   1.1962   0.03304   0.02319  -0.0107   0.1078   1.0000
  10.750   1.2098   0.03400   0.02413  -0.0096   0.1052   1.0000
  11.000   1.2221   0.03503   0.02533  -0.0084   0.1019   1.0000
  11.250   1.2333   0.03615   0.02649  -0.0072   0.0986   1.0000
  11.500   1.2433   0.03735   0.02787  -0.0060   0.0952   1.0000
  11.750   1.2520   0.03866   0.02936  -0.0048   0.0917   1.0000
  12.000   1.2591   0.04006   0.03093  -0.0037   0.0878   1.0000
  12.250   1.2656   0.04159   0.03271  -0.0027   0.0835   1.0000
  12.500   1.2741   0.04334   0.03488  -0.0019   0.0766   1.0000
  12.750   1.2820   0.04531   0.03720  -0.0011   0.0690   1.0000
  13.000   1.2875   0.04701   0.03901  -0.0006   0.0653   1.0000
  13.250   1.2921   0.04871   0.04078  -0.0003   0.0632   1.0000
  13.500   1.2947   0.05067   0.04278  -0.0001   0.0617   1.0000
  13.750   1.2952   0.05302   0.04514  -0.0002   0.0604   1.0000
  14.000   1.2934   0.05579   0.04796  -0.0006   0.0594   1.0000
  14.250   1.2885   0.05915   0.05139  -0.0012   0.0585   1.0000
  14.500   1.2814   0.06296   0.05530  -0.0022   0.0577   1.0000
  14.750   1.2719   0.06729   0.05973  -0.0036   0.0571   1.0000
  15.000   1.2603   0.07216   0.06471  -0.0055   0.0566   1.0000
  15.250   1.2474   0.07758   0.07023  -0.0080   0.0562   1.0000
  15.500   1.2319   0.08382   0.07664  -0.0110   0.0559   1.0000
  15.750   1.2141   0.09090   0.08391  -0.0148   0.0555   1.0000
  16.000   1.1938   0.09891   0.09211  -0.0193   0.0553   1.0000
  16.250   1.1720   0.10762   0.10101  -0.0243   0.0550   1.0000
  16.500   1.1504   0.11662   0.11018  -0.0296   0.0547   1.0000
  16.750   1.1292   0.12572   0.11945  -0.0349   0.0544   1.0000
  17.000   1.1080   0.13505   0.12892  -0.0403   0.0539   1.0000
  17.250   1.1000   0.14133   0.13527  -0.0439   0.0534   1.0000
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