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NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD B (n64212mb-il)
Reynolds number: 50,000
Max Cl/Cd: 25.25 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212mb-il-50000-n5.txt
Download as CSV file: xf-n64212mb-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD B                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5865   0.08780   0.08020  -0.0342   1.0000   0.0566
 -10.500  -0.5969   0.08242   0.07481  -0.0372   1.0000   0.0563
 -10.250  -0.6119   0.07721   0.06956  -0.0401   1.0000   0.0559
 -10.000  -0.6285   0.07263   0.06492  -0.0419   1.0000   0.0555
  -9.750  -0.6459   0.06875   0.06095  -0.0423   1.0000   0.0552
  -9.500  -0.6598   0.06503   0.05709  -0.0420   1.0000   0.0550
  -9.250  -0.6689   0.06138   0.05323  -0.0414   1.0000   0.0548
  -9.000  -0.6738   0.05788   0.04948  -0.0405   1.0000   0.0547
  -8.750  -0.6745   0.05455   0.04586  -0.0394   1.0000   0.0547
  -8.500  -0.6718   0.05138   0.04236  -0.0381   1.0000   0.0548
  -8.250  -0.6659   0.04844   0.03909  -0.0367   1.0000   0.0552
  -8.000  -0.6580   0.04576   0.03601  -0.0351   1.0000   0.0560
  -7.750  -0.6481   0.04330   0.03318  -0.0334   1.0000   0.0571
  -7.500  -0.6334   0.04131   0.03116  -0.0321   1.0000   0.0585
  -7.250  -0.6186   0.03950   0.02923  -0.0306   1.0000   0.0599
  -7.000  -0.6032   0.03767   0.02720  -0.0290   1.0000   0.0612
  -6.750  -0.5866   0.03592   0.02523  -0.0273   1.0000   0.0624
  -6.500  -0.5695   0.03437   0.02347  -0.0256   1.0000   0.0643
  -6.250  -0.5521   0.03300   0.02189  -0.0237   1.0000   0.0669
  -6.000  -0.5351   0.03178   0.02073  -0.0221   1.0000   0.0697
  -5.750  -0.5177   0.03071   0.01963  -0.0202   1.0000   0.0727
  -5.500  -0.5003   0.02977   0.01857  -0.0182   1.0000   0.0760
  -5.250  -0.4849   0.02885   0.01768  -0.0161   1.0000   0.0800
  -5.000  -0.4707   0.02803   0.01686  -0.0140   1.0000   0.0849
  -4.750  -0.4562   0.02731   0.01602  -0.0119   1.0000   0.0904
  -4.500  -0.4435   0.02642   0.01522  -0.0100   1.0000   0.0975
  -4.250  -0.4296   0.02560   0.01440  -0.0082   1.0000   0.1067
  -4.000  -0.4142   0.02471   0.01356  -0.0069   0.9996   0.1214
  -3.750  -0.3841   0.02313   0.01240  -0.0089   0.9924   0.1702
  -3.500  -0.3657   0.02091   0.01222  -0.0085   0.9853   0.4860
  -3.250  -0.3405   0.02125   0.01279  -0.0069   0.9771   0.6057
  -3.000  -0.3183   0.02205   0.01370  -0.0040   0.9692   0.6822
  -2.750  -0.3016   0.02332   0.01512   0.0018   0.9614   0.7424
  -2.500  -0.2808   0.02400   0.01574   0.0053   0.9539   0.7772
  -2.250  -0.2495   0.02404   0.01558   0.0047   0.9475   0.7911
  -2.000  -0.2211   0.02398   0.01535   0.0042   0.9404   0.8038
  -1.750  -0.1898   0.02400   0.01522   0.0034   0.9338   0.8135
  -1.500  -0.1563   0.02398   0.01505   0.0019   0.9282   0.8236
  -1.250  -0.1294   0.02394   0.01491   0.0017   0.9200   0.8338
  -1.000  -0.0873   0.02390   0.01474  -0.0009   0.9098   0.8423
  -0.750  -0.0368   0.02370   0.01441  -0.0045   0.8930   0.8503
  -0.500   0.0095   0.02335   0.01395  -0.0069   0.8722   0.8578
  -0.250   0.0511   0.02298   0.01351  -0.0084   0.8533   0.8661
   0.000   0.0874   0.02267   0.01314  -0.0092   0.8365   0.8748
   0.250   0.1214   0.02233   0.01277  -0.0095   0.8192   0.8844
   0.500   0.1564   0.02197   0.01238  -0.0100   0.8003   0.8933
   0.750   0.1879   0.02159   0.01197  -0.0097   0.7798   0.9040
   1.000   0.2223   0.02117   0.01152  -0.0099   0.7544   0.9133
   1.250   0.2551   0.02073   0.01104  -0.0098   0.7231   0.9237
   1.500   0.2859   0.02039   0.01067  -0.0097   0.6847   0.9353
   1.750   0.3205   0.02005   0.01025  -0.0101   0.6293   0.9462
   2.000   0.3560   0.01986   0.00963  -0.0104   0.5102   0.9562
   2.250   0.3852   0.02055   0.00924  -0.0105   0.3863   0.9674
   2.500   0.4198   0.02133   0.00955  -0.0127   0.3467   0.9792
   2.750   0.4562   0.02199   0.00995  -0.0152   0.3251   0.9921
   3.000   0.4808   0.02248   0.01030  -0.0155   0.3113   1.0000
   3.250   0.4931   0.02290   0.01061  -0.0134   0.3023   1.0000
   3.500   0.5075   0.02330   0.01095  -0.0115   0.2936   1.0000
   3.750   0.5253   0.02380   0.01132  -0.0102   0.2865   1.0000
   4.000   0.5470   0.02428   0.01180  -0.0094   0.2796   1.0000
   4.250   0.5714   0.02486   0.01231  -0.0091   0.2736   1.0000
   4.500   0.5972   0.02547   0.01288  -0.0090   0.2678   1.0000
   4.750   0.6232   0.02609   0.01352  -0.0089   0.2616   1.0000
   5.000   0.6500   0.02678   0.01415  -0.0089   0.2562   1.0000
   5.250   0.6771   0.02754   0.01490  -0.0090   0.2516   1.0000
   5.500   0.7039   0.02832   0.01580  -0.0091   0.2473   1.0000
   5.750   0.7305   0.02916   0.01670  -0.0091   0.2429   1.0000
   6.000   0.7573   0.03004   0.01755  -0.0092   0.2389   1.0000
   6.250   0.7831   0.03101   0.01859  -0.0092   0.2348   1.0000
   6.500   0.8073   0.03202   0.01984  -0.0091   0.2305   1.0000
   6.750   0.8321   0.03312   0.02108  -0.0090   0.2270   1.0000
   7.000   0.8570   0.03422   0.02226  -0.0089   0.2236   1.0000
   7.250   0.8829   0.03538   0.02341  -0.0090   0.2203   1.0000
   7.500   0.9027   0.03677   0.02515  -0.0085   0.2163   1.0000
   7.750   0.9232   0.03823   0.02688  -0.0081   0.2124   1.0000
   8.000   0.9442   0.03966   0.02849  -0.0077   0.2089   1.0000
   8.250   0.9670   0.04096   0.02988  -0.0075   0.2054   1.0000
   8.500   0.9859   0.04261   0.03172  -0.0070   0.2018   1.0000
   8.750   0.9971   0.04471   0.03425  -0.0060   0.1976   1.0000
   9.000   1.0114   0.04656   0.03637  -0.0053   0.1934   1.0000
   9.250   1.0314   0.04791   0.03780  -0.0049   0.1893   1.0000
   9.500   1.0463   0.04976   0.03982  -0.0042   0.1855   1.0000
   9.750   1.0422   0.05286   0.04340  -0.0026   0.1810   1.0000
  10.000   1.0472   0.05514   0.04592  -0.0015   0.1764   1.0000
  10.250   1.0693   0.05613   0.04694  -0.0011   0.1722   1.0000
  10.500   1.0630   0.05925   0.05034   0.0003   0.1685   1.0000
  10.750   1.0289   0.06418   0.05563   0.0023   0.1657   1.0000
  11.000   0.9831   0.07027   0.06190   0.0029   0.1639   1.0000
  11.250   0.9014   0.08314   0.07487  -0.0031   0.1628   1.0000
  11.500   0.8681   0.09258   0.08434  -0.0087   0.1588   1.0000
  11.750   0.9456   0.08366   0.07551  -0.0006   0.1545   1.0000
  12.000   0.8196   0.11060   0.10234  -0.0194   0.1500   1.0000
  12.250   0.8104   0.11663   0.10838  -0.0226   0.1452   1.0000
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