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NACA 64-215 AIRFOIL (n64215-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-215 AIRFOIL (n64215-il)
Reynolds number: 50,000
Max Cl/Cd: 26.61 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64215-il-50000-n5.txt
Download as CSV file: xf-n64215-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-215 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5944   0.10703   0.09935  -0.0372   1.0000   0.0615
 -12.750  -0.6101   0.09931   0.09162  -0.0417   1.0000   0.0612
 -12.500  -0.6325   0.09142   0.08369  -0.0466   1.0000   0.0609
 -12.250  -0.6559   0.08437   0.07656  -0.0507   1.0000   0.0605
 -12.000  -0.6802   0.07815   0.07023  -0.0540   1.0000   0.0602
 -11.750  -0.7034   0.07284   0.06477  -0.0562   1.0000   0.0600
 -11.500  -0.7249   0.06827   0.06002  -0.0574   1.0000   0.0600
 -11.250  -0.7432   0.06442   0.05598  -0.0574   1.0000   0.0600
 -11.000  -0.7588   0.06110   0.05245  -0.0565   1.0000   0.0601
 -10.750  -0.7720   0.05816   0.04929  -0.0546   1.0000   0.0604
 -10.500  -0.7791   0.05527   0.04611  -0.0529   1.0000   0.0607
 -10.250  -0.7818   0.05247   0.04298  -0.0511   1.0000   0.0612
 -10.000  -0.7768   0.04992   0.04023  -0.0496   1.0000   0.0622
  -9.750  -0.7651   0.04791   0.03819  -0.0486   1.0000   0.0639
  -9.500  -0.7550   0.04606   0.03622  -0.0472   1.0000   0.0660
  -9.250  -0.7449   0.04418   0.03415  -0.0455   1.0000   0.0680
  -9.000  -0.7333   0.04234   0.03207  -0.0438   1.0000   0.0699
  -8.750  -0.7194   0.04063   0.03009  -0.0419   1.0000   0.0717
  -8.500  -0.7029   0.03915   0.02862  -0.0405   1.0000   0.0745
  -8.250  -0.6902   0.03807   0.02753  -0.0385   1.0000   0.0777
  -8.000  -0.6765   0.03705   0.02641  -0.0364   1.0000   0.0812
  -7.750  -0.6610   0.03614   0.02530  -0.0341   1.0000   0.0846
  -7.500  -0.6506   0.03529   0.02459  -0.0316   1.0000   0.0884
  -7.250  -0.6456   0.03463   0.02392  -0.0285   1.0000   0.0927
  -7.000  -0.6320   0.03386   0.02301  -0.0267   0.9977   0.0986
  -6.750  -0.6017   0.03257   0.02178  -0.0284   0.9878   0.1080
  -6.500  -0.5742   0.03124   0.02049  -0.0300   0.9776   0.1220
  -6.250  -0.5495   0.02979   0.01912  -0.0313   0.9670   0.1426
  -6.000  -0.5292   0.02796   0.01764  -0.0326   0.9562   0.1809
  -5.750  -0.5136   0.02567   0.01626  -0.0335   0.9460   0.2873
  -5.500  -0.4959   0.02550   0.01710  -0.0312   0.9352   0.4600
  -5.250  -0.4672   0.02606   0.01756  -0.0308   0.9262   0.5308
  -5.000  -0.4381   0.02687   0.01823  -0.0299   0.9176   0.5754
  -4.750  -0.4095   0.02804   0.01929  -0.0280   0.9091   0.6092
  -4.500  -0.3796   0.02904   0.02014  -0.0266   0.9013   0.6390
  -4.250  -0.3474   0.03002   0.02099  -0.0251   0.8940   0.6583
  -4.000  -0.3189   0.03028   0.02105  -0.0246   0.8859   0.6737
  -3.750  -0.2864   0.03050   0.02109  -0.0246   0.8788   0.6834
  -3.500  -0.2622   0.03031   0.02074  -0.0243   0.8700   0.6930
  -3.250  -0.2343   0.03017   0.02042  -0.0245   0.8627   0.7009
  -3.000  -0.2128   0.02992   0.02003  -0.0240   0.8538   0.7091
  -2.750  -0.1827   0.02979   0.01975  -0.0244   0.8475   0.7157
  -2.500  -0.1668   0.02952   0.01937  -0.0233   0.8380   0.7245
  -2.250  -0.1338   0.02942   0.01913  -0.0240   0.8328   0.7300
  -2.000  -0.1200   0.02924   0.01887  -0.0226   0.8230   0.7384
  -1.750  -0.0904   0.02910   0.01862  -0.0230   0.8174   0.7439
  -1.500  -0.0704   0.02907   0.01852  -0.0222   0.8095   0.7503
  -1.250  -0.0487   0.02886   0.01822  -0.0220   0.8027   0.7579
  -1.000  -0.0188   0.02879   0.01808  -0.0224   0.7976   0.7628
  -0.750  -0.0032   0.02882   0.01807  -0.0211   0.7889   0.7700
  -0.500   0.0238   0.02871   0.01790  -0.0214   0.7839   0.7765
  -0.250   0.0443   0.02882   0.01799  -0.0207   0.7772   0.7827
   0.000   0.0640   0.02879   0.01792  -0.0202   0.7704   0.7909
   0.250   0.0943   0.02878   0.01789  -0.0205   0.7662   0.7963
   0.500   0.1077   0.02900   0.01812  -0.0191   0.7583   0.8049
   0.750   0.1314   0.02911   0.01824  -0.0188   0.7529   0.8118
   1.000   0.1602   0.02911   0.01823  -0.0191   0.7490   0.8191
   1.250   0.1719   0.02948   0.01864  -0.0174   0.7409   0.8278
   1.500   0.1958   0.02962   0.01880  -0.0171   0.7357   0.8363
   1.750   0.2252   0.02966   0.01887  -0.0175   0.7322   0.8443
   2.000   0.2336   0.03020   0.01947  -0.0155   0.7238   0.8553
   2.250   0.2603   0.03037   0.01970  -0.0156   0.7189   0.8637
   2.500   0.2903   0.03041   0.01979  -0.0161   0.7153   0.8735
   2.750   0.2993   0.03108   0.02056  -0.0143   0.7063   0.8856
   3.000   0.3301   0.03122   0.02078  -0.0150   0.7015   0.8954
   3.250   0.3549   0.03154   0.02121  -0.0151   0.6957   0.9074
   3.500   0.3764   0.03204   0.02182  -0.0152   0.6879   0.9208
   3.750   0.4164   0.03211   0.02202  -0.0174   0.6837   0.9310
   4.000   0.4415   0.03283   0.02289  -0.0186   0.6752   0.9452
   4.250   0.4825   0.03307   0.02330  -0.0215   0.6693   0.9564
   4.500   0.5271   0.03317   0.02358  -0.0247   0.6641   0.9670
   4.750   0.5604   0.03386   0.02446  -0.0275   0.6541   0.9824
   5.000   0.6138   0.03339   0.02421  -0.0311   0.6490   0.9919
   5.250   0.6063   0.03419   0.02507  -0.0272   0.6364   1.0000
   5.500   0.6105   0.03460   0.02552  -0.0243   0.6252   1.0000
   5.750   0.6494   0.03374   0.02482  -0.0245   0.6171   1.0000
   6.000   0.6630   0.03392   0.02511  -0.0226   0.6030   1.0000
   6.250   0.6878   0.03340   0.02472  -0.0212   0.5878   1.0000
   6.500   0.7232   0.03192   0.02339  -0.0201   0.5695   1.0000
   6.750   0.7451   0.03108   0.02268  -0.0179   0.5468   1.0000
   7.000   0.7705   0.02985   0.02155  -0.0157   0.5196   1.0000
   7.250   0.7806   0.02970   0.02148  -0.0128   0.4879   1.0000
   7.500   0.7829   0.03012   0.02198  -0.0097   0.4509   1.0000
   7.750   0.7890   0.03041   0.02224  -0.0068   0.3934   1.0000
   8.000   0.8042   0.03022   0.02116  -0.0034   0.2877   1.0000
   8.250   0.7984   0.03230   0.02265  -0.0008   0.2265   1.0000
   8.500   0.7935   0.03470   0.02464   0.0011   0.1859   1.0000
   8.750   0.7918   0.03706   0.02671   0.0025   0.1580   1.0000
   9.000   0.7941   0.03925   0.02872   0.0036   0.1370   1.0000
   9.250   0.7994   0.04127   0.03062   0.0046   0.1224   1.0000
   9.500   0.8074   0.04315   0.03242   0.0056   0.1110   1.0000
   9.750   0.8172   0.04492   0.03407   0.0064   0.1019   1.0000
  10.000   0.8337   0.04632   0.03557   0.0074   0.0936   1.0000
  10.250   0.8512   0.04772   0.03689   0.0082   0.0871   1.0000
  10.500   0.8735   0.04894   0.03829   0.0090   0.0807   1.0000
  10.750   0.9031   0.04999   0.03924   0.0096   0.0757   1.0000
  11.000   0.9285   0.05152   0.04108   0.0102   0.0708   1.0000
  11.250   0.9517   0.05316   0.04279   0.0105   0.0671   1.0000
  11.500   0.9802   0.05512   0.04482   0.0107   0.0643   1.0000
  11.750   0.9916   0.05777   0.04786   0.0112   0.0620   1.0000
  12.000   0.9990   0.06051   0.05086   0.0116   0.0598   1.0000
  12.250   1.0049   0.06329   0.05385   0.0120   0.0581   1.0000
  12.500   1.0102   0.06620   0.05694   0.0122   0.0569   1.0000
  12.750   1.0144   0.06939   0.06029   0.0123   0.0559   1.0000
  13.000   1.0174   0.07285   0.06391   0.0122   0.0552   1.0000
  13.250   1.0043   0.07727   0.06861   0.0118   0.0549   1.0000
  13.500   0.9871   0.08222   0.07386   0.0107   0.0547   1.0000
  13.750   0.9671   0.08776   0.07967   0.0089   0.0546   1.0000
  14.000   0.9433   0.09419   0.08635   0.0062   0.0546   1.0000
  14.250   0.9200   0.10114   0.09348   0.0027   0.0548   1.0000
  14.500   0.8957   0.10894   0.10144  -0.0016   0.0550   1.0000
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