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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 200,000
Max Cl/Cd: 39.88 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012a-il-200000-n5.txt
Download as CSV file: xf-n64012a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-012A AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8238   0.08751   0.08362  -0.0158   1.0000   0.0168
 -13.000  -0.8478   0.07892   0.07490  -0.0216   1.0000   0.0167
 -12.750  -0.8710   0.07157   0.06738  -0.0261   1.0000   0.0166
 -12.500  -0.8935   0.06519   0.06079  -0.0294   1.0000   0.0166
 -12.250  -0.9145   0.05974   0.05509  -0.0314   1.0000   0.0166
 -12.000  -0.9335   0.05512   0.05020  -0.0320   1.0000   0.0167
 -11.750  -0.9500   0.05120   0.04602  -0.0315   1.0000   0.0168
 -11.500  -0.9598   0.04801   0.04265  -0.0303   1.0000   0.0170
 -11.250  -0.9637   0.04565   0.04014  -0.0286   1.0000   0.0173
 -11.000  -0.9647   0.04367   0.03802  -0.0266   1.0000   0.0176
 -10.750  -0.9628   0.04177   0.03595  -0.0245   1.0000   0.0179
 -10.500  -0.9579   0.03967   0.03362  -0.0227   1.0000   0.0182
 -10.250  -0.9508   0.03745   0.03112  -0.0210   1.0000   0.0185
 -10.000  -0.9407   0.03535   0.02876  -0.0194   1.0000   0.0188
  -9.750  -0.9280   0.03337   0.02654  -0.0179   1.0000   0.0192
  -9.500  -0.9131   0.03152   0.02443  -0.0166   1.0000   0.0197
  -9.250  -0.8964   0.02984   0.02252  -0.0154   1.0000   0.0203
  -9.000  -0.8783   0.02846   0.02092  -0.0143   1.0000   0.0211
  -8.750  -0.8591   0.02722   0.01946  -0.0133   1.0000   0.0218
  -8.500  -0.8395   0.02576   0.01783  -0.0123   1.0000   0.0223
  -8.250  -0.8205   0.02430   0.01630  -0.0113   1.0000   0.0229
  -8.000  -0.8013   0.02321   0.01517  -0.0102   1.0000   0.0236
  -7.750  -0.7823   0.02227   0.01418  -0.0091   1.0000   0.0243
  -7.500  -0.7635   0.02138   0.01324  -0.0078   1.0000   0.0252
  -7.250  -0.7453   0.02054   0.01233  -0.0064   1.0000   0.0262
  -7.000  -0.7277   0.01977   0.01150  -0.0048   1.0000   0.0273
  -6.750  -0.7100   0.01915   0.01080  -0.0032   1.0000   0.0286
  -6.500  -0.6956   0.01832   0.00998  -0.0011   1.0000   0.0304
  -6.250  -0.6800   0.01771   0.00936   0.0008   1.0000   0.0323
  -6.000  -0.6591   0.01711   0.00870   0.0016   0.9978   0.0346
  -5.750  -0.6258   0.01645   0.00796   0.0000   0.9907   0.0378
  -5.500  -0.5931   0.01572   0.00724  -0.0017   0.9833   0.0440
  -5.250  -0.5609   0.01512   0.00663  -0.0031   0.9747   0.0531
  -5.000  -0.5301   0.01454   0.00608  -0.0042   0.9648   0.0679
  -4.750  -0.5004   0.01388   0.00556  -0.0052   0.9545   0.0981
  -4.500  -0.4731   0.01295   0.00501  -0.0059   0.9438   0.1734
  -4.250  -0.4497   0.01173   0.00441  -0.0060   0.9323   0.3084
  -4.000  -0.4294   0.01077   0.00412  -0.0051   0.9192   0.4586
  -3.750  -0.4037   0.01047   0.00400  -0.0047   0.9074   0.5242
  -3.500  -0.3770   0.01029   0.00389  -0.0043   0.8961   0.5655
  -3.250  -0.3499   0.01018   0.00379  -0.0040   0.8853   0.5964
  -3.000  -0.3241   0.01010   0.00376  -0.0033   0.8740   0.6290
  -2.750  -0.2988   0.01007   0.00377  -0.0025   0.8628   0.6590
  -2.500  -0.2723   0.01004   0.00370  -0.0020   0.8524   0.6764
  -2.250  -0.2453   0.01000   0.00361  -0.0017   0.8424   0.6883
  -2.000  -0.2183   0.00996   0.00353  -0.0014   0.8320   0.6972
  -1.750  -0.1910   0.00992   0.00342  -0.0012   0.8225   0.7059
  -1.500  -0.1637   0.00989   0.00334  -0.0010   0.8130   0.7128
  -1.250  -0.1365   0.00986   0.00326  -0.0009   0.8034   0.7212
  -1.000  -0.1091   0.00984   0.00321  -0.0006   0.7951   0.7283
  -0.750  -0.0819   0.00982   0.00316  -0.0005   0.7857   0.7365
  -0.500  -0.0546   0.00981   0.00313  -0.0003   0.7771   0.7439
  -0.250  -0.0273   0.00980   0.00310  -0.0002   0.7685   0.7524
   0.000   0.0000   0.00980   0.00311   0.0000   0.7603   0.7603
   0.250   0.0273   0.00980   0.00310   0.0002   0.7524   0.7685
   0.500   0.0546   0.00981   0.00313   0.0003   0.7439   0.7771
   0.750   0.0819   0.00982   0.00316   0.0005   0.7364   0.7857
   1.000   0.1092   0.00984   0.00321   0.0006   0.7283   0.7951
   1.250   0.1365   0.00986   0.00326   0.0009   0.7212   0.8034
   1.500   0.1637   0.00989   0.00334   0.0010   0.7128   0.8130
   1.750   0.1910   0.00992   0.00342   0.0012   0.7059   0.8225
   2.000   0.2183   0.00996   0.00353   0.0014   0.6972   0.8320
   2.250   0.2453   0.01000   0.00361   0.0017   0.6883   0.8424
   2.500   0.2723   0.01004   0.00370   0.0020   0.6764   0.8524
   2.750   0.2988   0.01007   0.00377   0.0025   0.6590   0.8628
   3.000   0.3241   0.01010   0.00376   0.0033   0.6290   0.8740
   3.250   0.3499   0.01018   0.00379   0.0040   0.5963   0.8853
   3.500   0.3770   0.01029   0.00389   0.0043   0.5655   0.8961
   3.750   0.4037   0.01047   0.00400   0.0047   0.5241   0.9074
   4.000   0.4295   0.01077   0.00412   0.0051   0.4588   0.9193
   4.250   0.4497   0.01173   0.00441   0.0060   0.3085   0.9323
   4.500   0.4731   0.01295   0.00501   0.0059   0.1736   0.9438
   4.750   0.5004   0.01388   0.00556   0.0052   0.0981   0.9544
   5.000   0.5301   0.01454   0.00608   0.0042   0.0679   0.9647
   5.250   0.5609   0.01512   0.00663   0.0031   0.0531   0.9747
   5.500   0.5930   0.01572   0.00724   0.0017   0.0440   0.9833
   5.750   0.6258   0.01645   0.00796   0.0000   0.0379   0.9907
   6.000   0.6590   0.01711   0.00870  -0.0016   0.0346   0.9978
   6.250   0.6800   0.01771   0.00936  -0.0008   0.0323   1.0000
   6.500   0.6956   0.01832   0.00997   0.0011   0.0304   1.0000
   6.750   0.7100   0.01915   0.01080   0.0032   0.0286   1.0000
   7.000   0.7277   0.01977   0.01150   0.0048   0.0273   1.0000
   7.250   0.7453   0.02054   0.01233   0.0064   0.0262   1.0000
   7.500   0.7635   0.02138   0.01324   0.0078   0.0252   1.0000
   7.750   0.7823   0.02226   0.01418   0.0091   0.0243   1.0000
   8.000   0.8014   0.02321   0.01517   0.0102   0.0236   1.0000
   8.250   0.8205   0.02430   0.01630   0.0113   0.0229   1.0000
   8.500   0.8396   0.02576   0.01783   0.0123   0.0223   1.0000
   8.750   0.8592   0.02722   0.01946   0.0133   0.0218   1.0000
   9.000   0.8784   0.02846   0.02091   0.0143   0.0211   1.0000
   9.250   0.8965   0.02984   0.02252   0.0154   0.0203   1.0000
   9.500   0.9132   0.03152   0.02443   0.0166   0.0197   1.0000
   9.750   0.9281   0.03338   0.02654   0.0179   0.0192   1.0000
  10.000   0.9408   0.03535   0.02877   0.0193   0.0188   1.0000
  10.250   0.9510   0.03745   0.03113   0.0209   0.0185   1.0000
  10.500   0.9582   0.03967   0.03362   0.0227   0.0182   1.0000
  10.750   0.9632   0.04177   0.03594   0.0245   0.0179   1.0000
  11.000   0.9650   0.04369   0.03803   0.0265   0.0176   1.0000
  11.250   0.9642   0.04564   0.04013   0.0285   0.0173   1.0000
  11.500   0.9603   0.04803   0.04266   0.0302   0.0170   1.0000
  11.750   0.9504   0.05124   0.04606   0.0314   0.0168   1.0000
  12.000   0.9340   0.05516   0.05024   0.0319   0.0167   1.0000
  12.250   0.9148   0.05982   0.05518   0.0312   0.0166   1.0000
  12.500   0.8937   0.06531   0.06092   0.0292   0.0166   1.0000
  12.750   0.8714   0.07169   0.06750   0.0259   0.0166   1.0000
  13.000   0.8478   0.07915   0.07514   0.0212   0.0167   1.0000
  13.250   0.8241   0.08775   0.08387   0.0154   0.0168   1.0000
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