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NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
Reynolds number: 500,000
Max Cl/Cd: 56.48 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64012-il-500000.txt
Download as CSV file: xf-n64012-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY 64-012 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8334   0.07142   0.06878  -0.0225   1.0000   0.0202
 -12.000  -0.8534   0.06580   0.06307  -0.0253   1.0000   0.0197
 -11.750  -0.8802   0.05994   0.05706  -0.0274   1.0000   0.0192
 -11.500  -0.9031   0.05528   0.05222  -0.0280   1.0000   0.0192
 -11.250  -0.9290   0.05065   0.04737  -0.0271   1.0000   0.0188
 -11.000  -0.9453   0.04756   0.04409  -0.0250   1.0000   0.0190
 -10.750  -0.9657   0.04385   0.04012  -0.0214   1.0000   0.0187
 -10.500  -0.9746   0.03998   0.03592  -0.0187   1.0000   0.0188
 -10.250  -0.9780   0.03590   0.03144  -0.0163   1.0000   0.0186
 -10.000  -0.9717   0.03283   0.02804  -0.0145   1.0000   0.0187
  -9.750  -0.9601   0.03013   0.02503  -0.0130   1.0000   0.0189
  -9.500  -0.9445   0.02801   0.02267  -0.0119   1.0000   0.0192
  -9.250  -0.9264   0.02613   0.02055  -0.0109   1.0000   0.0196
  -9.000  -0.9062   0.02476   0.01899  -0.0102   1.0000   0.0202
  -8.750  -0.8846   0.02414   0.01821  -0.0095   1.0000   0.0207
  -8.500  -0.8637   0.02171   0.01560  -0.0089   1.0000   0.0213
  -8.250  -0.8420   0.02010   0.01394  -0.0084   1.0000   0.0219
  -8.000  -0.8197   0.01913   0.01295  -0.0079   1.0000   0.0225
  -7.750  -0.7969   0.01831   0.01209  -0.0075   1.0000   0.0233
  -7.500  -0.7741   0.01750   0.01125  -0.0070   1.0000   0.0240
  -7.250  -0.7515   0.01677   0.01047  -0.0065   1.0000   0.0249
  -7.000  -0.7258   0.01621   0.00987  -0.0065   0.9948   0.0261
  -6.750  -0.6924   0.01511   0.00869  -0.0084   0.9776   0.0274
  -6.500  -0.6619   0.01413   0.00768  -0.0097   0.9622   0.0292
  -6.250  -0.6362   0.01361   0.00711  -0.0095   0.9458   0.0309
  -6.000  -0.6146   0.01322   0.00664  -0.0084   0.9302   0.0328
  -5.750  -0.5937   0.01276   0.00609  -0.0071   0.9162   0.0348
  -5.500  -0.5728   0.01220   0.00550  -0.0059   0.9034   0.0388
  -5.250  -0.5491   0.01190   0.00513  -0.0052   0.8921   0.0426
  -5.000  -0.5265   0.01141   0.00460  -0.0042   0.8815   0.0494
  -4.750  -0.5026   0.01100   0.00419  -0.0036   0.8709   0.0608
  -4.500  -0.4801   0.01030   0.00373  -0.0029   0.8608   0.1110
  -4.250  -0.4612   0.00912   0.00315  -0.0021   0.8513   0.2521
  -4.000  -0.4429   0.00784   0.00267  -0.0011   0.8412   0.4423
  -3.750  -0.4177   0.00755   0.00256  -0.0007   0.8320   0.5067
  -3.500  -0.3914   0.00743   0.00245  -0.0003   0.8236   0.5399
  -3.250  -0.3639   0.00735   0.00237  -0.0003   0.8144   0.5626
  -3.000  -0.3365   0.00731   0.00229  -0.0001   0.8066   0.5787
  -2.750  -0.3087   0.00726   0.00223  -0.0001   0.7977   0.5943
  -2.500  -0.2813   0.00723   0.00218   0.0001   0.7898   0.6119
  -2.250  -0.2540   0.00721   0.00220   0.0004   0.7811   0.6334
  -2.000  -0.2266   0.00724   0.00222   0.0006   0.7730   0.6524
  -1.750  -0.1986   0.00721   0.00217   0.0006   0.7647   0.6616
  -1.500  -0.1702   0.00721   0.00212   0.0005   0.7569   0.6695
  -1.250  -0.1421   0.00717   0.00208   0.0005   0.7492   0.6768
  -1.000  -0.1136   0.00718   0.00204   0.0004   0.7415   0.6847
  -0.750  -0.0854   0.00714   0.00201   0.0003   0.7340   0.6910
  -0.500  -0.0569   0.00714   0.00199   0.0002   0.7265   0.6983
  -0.250  -0.0285   0.00712   0.00196   0.0001   0.7189   0.7047
   0.000  -0.0001   0.00713   0.00196   0.0000   0.7118   0.7118
   0.250   0.0284   0.00712   0.00196  -0.0001   0.7047   0.7189
   0.500   0.0567   0.00714   0.00199  -0.0002   0.6983   0.7265
   0.750   0.0852   0.00714   0.00201  -0.0003   0.6910   0.7340
   1.000   0.1135   0.00718   0.00204  -0.0003   0.6847   0.7415
   1.250   0.1420   0.00717   0.00208  -0.0005   0.6768   0.7492
   1.500   0.1700   0.00721   0.00212  -0.0005   0.6695   0.7569
   1.750   0.1985   0.00721   0.00217  -0.0006   0.6615   0.7647
   2.000   0.2264   0.00724   0.00222  -0.0005   0.6524   0.7730
   2.250   0.2539   0.00721   0.00220  -0.0003   0.6336   0.7811
   2.500   0.2811   0.00723   0.00218  -0.0001   0.6120   0.7898
   2.750   0.3085   0.00726   0.00223   0.0001   0.5944   0.7977
   3.000   0.3363   0.00731   0.00229   0.0001   0.5787   0.8066
   3.250   0.3637   0.00735   0.00237   0.0003   0.5626   0.8145
   3.500   0.3912   0.00743   0.00245   0.0004   0.5398   0.8236
   3.750   0.4176   0.00755   0.00256   0.0007   0.5069   0.8321
   4.000   0.4428   0.00784   0.00267   0.0011   0.4429   0.8413
   4.250   0.4611   0.00911   0.00315   0.0021   0.2531   0.8513
   4.500   0.4800   0.01029   0.00373   0.0030   0.1120   0.8608
   4.750   0.5025   0.01100   0.00419   0.0036   0.0609   0.8709
   5.000   0.5264   0.01140   0.00460   0.0043   0.0494   0.8815
   5.250   0.5490   0.01190   0.00513   0.0052   0.0427   0.8922
   5.500   0.5726   0.01220   0.00550   0.0060   0.0390   0.9035
   5.750   0.5935   0.01276   0.00610   0.0071   0.0348   0.9163
   6.000   0.6144   0.01322   0.00664   0.0084   0.0329   0.9303
   6.250   0.6360   0.01361   0.00711   0.0096   0.0310   0.9459
   6.500   0.6618   0.01412   0.00768   0.0097   0.0292   0.9623
   6.750   0.6923   0.01515   0.00873   0.0084   0.0273   0.9777
   7.000   0.7260   0.01619   0.00985   0.0065   0.0261   0.9949
   7.250   0.7515   0.01676   0.01046   0.0065   0.0250   1.0000
   7.500   0.7741   0.01750   0.01124   0.0070   0.0240   1.0000
   7.750   0.7969   0.01827   0.01205   0.0075   0.0232   1.0000
   8.000   0.8195   0.01911   0.01292   0.0080   0.0225   1.0000
   8.250   0.8419   0.02009   0.01393   0.0084   0.0219   1.0000
   8.500   0.8635   0.02170   0.01559   0.0090   0.0213   1.0000
   8.750   0.8844   0.02400   0.01807   0.0096   0.0207   1.0000
   9.000   0.9059   0.02482   0.01906   0.0102   0.0202   1.0000
   9.250   0.9262   0.02613   0.02055   0.0110   0.0196   1.0000
   9.500   0.9443   0.02800   0.02266   0.0119   0.0193   1.0000
   9.750   0.9598   0.03016   0.02507   0.0131   0.0189   1.0000
  10.000   0.9716   0.03276   0.02797   0.0145   0.0187   1.0000
  10.250   0.9765   0.03618   0.03174   0.0165   0.0187   1.0000
  10.500   0.9742   0.04000   0.03593   0.0188   0.0187   1.0000
  10.750   0.9633   0.04420   0.04049   0.0216   0.0190   1.0000
  11.000   0.9435   0.04777   0.04432   0.0251   0.0191   1.0000
  11.250   0.9236   0.05138   0.04812   0.0272   0.0193   1.0000
  11.500   0.9025   0.05535   0.05229   0.0280   0.0192   1.0000
  11.750   0.8802   0.06004   0.05713   0.0274   0.0198   1.0000
  12.000   0.8555   0.06554   0.06278   0.0255   0.0199   1.0000
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