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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 100,000
Max Cl/Cd: 48.17 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212-il-100000.txt
Download as CSV file: xf-n64212-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5628   0.11061   0.10561  -0.0249   1.0000   0.1327
 -10.500  -0.5180   0.10770   0.10258  -0.0182   1.0000   0.1391
 -10.250  -0.5474   0.10315   0.09818  -0.0249   1.0000   0.1468
 -10.000  -0.5273   0.09923   0.09422  -0.0226   1.0000   0.1508
  -9.750  -0.5211   0.09603   0.09104  -0.0229   1.0000   0.1581
  -9.500  -0.5382   0.09090   0.08602  -0.0268   1.0000   0.1647
  -9.250  -0.5231   0.08824   0.08334  -0.0254   1.0000   0.1715
  -9.000  -0.5415   0.08316   0.07838  -0.0290   1.0000   0.1801
  -7.250  -0.6611   0.04004   0.03267  -0.0340   1.0000   0.0751
  -7.000  -0.6529   0.03711   0.02953  -0.0316   1.0000   0.0739
  -6.750  -0.6439   0.03502   0.02709  -0.0291   1.0000   0.0744
  -6.500  -0.6326   0.03309   0.02483  -0.0268   1.0000   0.0749
  -6.250  -0.6189   0.03112   0.02254  -0.0248   1.0000   0.0750
  -6.000  -0.6033   0.02929   0.02042  -0.0230   1.0000   0.0753
  -5.750  -0.5864   0.02779   0.01865  -0.0213   1.0000   0.0759
  -5.500  -0.5684   0.02578   0.01657  -0.0200   1.0000   0.0782
  -5.250  -0.5510   0.02462   0.01543  -0.0188   1.0000   0.0824
  -5.000  -0.5323   0.02363   0.01436  -0.0175   1.0000   0.0862
  -4.750  -0.5132   0.02279   0.01336  -0.0161   1.0000   0.0897
  -4.500  -0.4841   0.02147   0.01225  -0.0171   0.9966   0.0982
  -4.250  -0.4463   0.02034   0.01124  -0.0195   0.9899   0.1114
  -4.000  -0.4071   0.01916   0.01024  -0.0226   0.9834   0.1408
  -3.750  -0.3874   0.01616   0.00972  -0.0224   0.9755   0.5703
  -3.500  -0.3548   0.01694   0.01056  -0.0220   0.9669   0.6590
  -3.250  -0.3222   0.01766   0.01125  -0.0216   0.9584   0.6979
  -3.000  -0.2953   0.01836   0.01192  -0.0200   0.9491   0.7293
  -2.750  -0.2669   0.01944   0.01302  -0.0174   0.9421   0.7670
  -2.500  -0.2500   0.02018   0.01376  -0.0132   0.9320   0.7953
  -2.250  -0.2132   0.02062   0.01409  -0.0134   0.9268   0.8131
  -2.000  -0.1896   0.02060   0.01398  -0.0128   0.9168   0.8239
  -1.750  -0.1452   0.02061   0.01386  -0.0158   0.9123   0.8322
  -1.500  -0.1222   0.02054   0.01369  -0.0154   0.9022   0.8428
  -1.250  -0.0792   0.02051   0.01357  -0.0181   0.8976   0.8508
  -1.000  -0.0577   0.02049   0.01349  -0.0175   0.8881   0.8602
  -0.750  -0.0183   0.02040   0.01332  -0.0198   0.8829   0.8688
  -0.500   0.0051   0.02041   0.01330  -0.0193   0.8738   0.8776
  -0.250   0.0406   0.02031   0.01315  -0.0210   0.8681   0.8869
   0.000   0.0669   0.02040   0.01322  -0.0211   0.8603   0.8961
   0.250   0.1017   0.02036   0.01315  -0.0226   0.8542   0.9052
   0.500   0.1302   0.02038   0.01316  -0.0232   0.8472   0.9160
   0.750   0.1689   0.02044   0.01323  -0.0256   0.8406   0.9241
   1.000   0.2131   0.02036   0.01316  -0.0287   0.8366   0.9327
   1.250   0.2424   0.02058   0.01342  -0.0300   0.8280   0.9444
   1.500   0.2960   0.02051   0.01340  -0.0351   0.8234   0.9499
   1.750   0.3403   0.02053   0.01347  -0.0387   0.8180   0.9589
   2.000   0.3909   0.02060   0.01363  -0.0438   0.8105   0.9658
   2.250   0.4411   0.02036   0.01347  -0.0480   0.8057   0.9730
   2.500   0.4842   0.02055   0.01379  -0.0520   0.7964   0.9826
   2.750   0.5355   0.02028   0.01363  -0.0565   0.7909   0.9899
   3.000   0.5794   0.02038   0.01389  -0.0607   0.7810   1.0000
   3.250   0.5946   0.02037   0.01395  -0.0586   0.7720   1.0000
   3.500   0.6088   0.02021   0.01385  -0.0560   0.7604   1.0000
   3.750   0.6223   0.01981   0.01349  -0.0526   0.7454   1.0000
   4.000   0.6393   0.01900   0.01269  -0.0491   0.7279   1.0000
   4.250   0.6504   0.01838   0.01212  -0.0449   0.7061   1.0000
   4.500   0.6722   0.01724   0.01090  -0.0414   0.6830   1.0000
   4.750   0.6861   0.01683   0.01054  -0.0381   0.6591   1.0000
   5.000   0.7065   0.01632   0.01005  -0.0357   0.6335   1.0000
   5.250   0.7266   0.01585   0.00963  -0.0332   0.5980   1.0000
   5.500   0.7442   0.01545   0.00914  -0.0302   0.5328   1.0000
   5.750   0.7349   0.01734   0.00927  -0.0239   0.2366   1.0000
   6.000   0.7342   0.02003   0.01097  -0.0204   0.1364   1.0000
   6.250   0.7479   0.02149   0.01224  -0.0185   0.1122   1.0000
   6.500   0.7650   0.02289   0.01352  -0.0170   0.0991   1.0000
   6.750   0.7858   0.02440   0.01491  -0.0160   0.0895   1.0000
   7.000   0.8103   0.02590   0.01629  -0.0156   0.0818   1.0000
   7.250   0.8400   0.02790   0.01831  -0.0157   0.0771   1.0000
   7.500   0.8670   0.02948   0.02001  -0.0155   0.0721   1.0000
   7.750   0.8952   0.03172   0.02221  -0.0158   0.0682   1.0000
   8.000   0.9236   0.03486   0.02553  -0.0159   0.0666   1.0000
   8.250   0.9466   0.03736   0.02840  -0.0151   0.0661   1.0000
   8.500   0.9666   0.04010   0.03154  -0.0140   0.0657   1.0000
   8.750   0.9827   0.04279   0.03467  -0.0126   0.0648   1.0000
   9.000   0.9958   0.04587   0.03819  -0.0111   0.0643   1.0000
   9.250   1.0072   0.04978   0.04245  -0.0097   0.0652   1.0000
   9.500   1.0209   0.05552   0.04834  -0.0093   0.0668   1.0000
   9.750   1.0009   0.05936   0.05330  -0.0043   0.0752   1.0000
  10.000   0.9329   0.05590   0.05046   0.0015   0.0776   1.0000
  10.250   0.8862   0.06095   0.05601   0.0056   0.0851   1.0000
  10.500   0.8485   0.06640   0.06165   0.0064   0.0874   1.0000
  10.750   0.8077   0.07442   0.06991   0.0049   0.0969   1.0000
  11.000   0.7634   0.08242   0.07802   0.0013   0.0970   1.0000
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