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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 500,000
Max Cl/Cd: 52.09 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012a-il-500000-n5.txt
Download as CSV file: xf-n64012a-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -1.0000   0.08866   0.08581  -0.0089   1.0000   0.0093
 -15.250  -1.0293   0.07851   0.07547  -0.0152   1.0000   0.0093
 -15.000  -1.0523   0.07055   0.06732  -0.0199   1.0000   0.0093
 -14.750  -1.0712   0.06400   0.06057  -0.0233   1.0000   0.0093
 -14.500  -1.0856   0.05853   0.05491  -0.0258   1.0000   0.0094
 -14.250  -1.0969   0.05387   0.05005  -0.0276   1.0000   0.0094
 -14.000  -1.1121   0.04901   0.04498  -0.0288   1.0000   0.0095
 -13.750  -1.1211   0.04521   0.04101  -0.0294   1.0000   0.0096
 -13.500  -1.1243   0.04227   0.03793  -0.0294   1.0000   0.0098
 -13.250  -1.1236   0.03990   0.03545  -0.0292   1.0000   0.0099
 -13.000  -1.1204   0.03793   0.03337  -0.0287   1.0000   0.0101
 -12.750  -1.1157   0.03619   0.03152  -0.0280   1.0000   0.0102
 -12.500  -1.1102   0.03455   0.02977  -0.0270   1.0000   0.0104
 -12.250  -1.1040   0.03302   0.02811  -0.0258   1.0000   0.0106
 -12.000  -1.0972   0.03153   0.02648  -0.0243   1.0000   0.0108
 -11.750  -1.0892   0.03012   0.02493  -0.0227   1.0000   0.0110
 -11.500  -1.0799   0.02879   0.02345  -0.0210   1.0000   0.0112
 -11.250  -1.0692   0.02756   0.02207  -0.0193   1.0000   0.0114
 -11.000  -1.0568   0.02639   0.02076  -0.0176   1.0000   0.0117
 -10.750  -1.0420   0.02527   0.01950  -0.0163   1.0000   0.0119
 -10.500  -1.0256   0.02429   0.01839  -0.0151   1.0000   0.0122
 -10.250  -1.0078   0.02343   0.01741  -0.0140   1.0000   0.0125
 -10.000  -0.9890   0.02267   0.01654  -0.0131   1.0000   0.0127
  -9.750  -0.9741   0.02131   0.01507  -0.0116   1.0000   0.0131
  -9.500  -0.9564   0.02040   0.01410  -0.0104   1.0000   0.0134
  -9.250  -0.9375   0.01964   0.01328  -0.0094   1.0000   0.0137
  -9.000  -0.9181   0.01895   0.01254  -0.0083   1.0000   0.0140
  -8.750  -0.8985   0.01829   0.01183  -0.0073   1.0000   0.0143
  -8.500  -0.8789   0.01766   0.01114  -0.0061   1.0000   0.0147
  -8.250  -0.8594   0.01707   0.01049  -0.0050   1.0000   0.0151
  -8.000  -0.8400   0.01654   0.00991  -0.0037   1.0000   0.0156
  -7.750  -0.8210   0.01604   0.00936  -0.0023   1.0000   0.0161
  -7.500  -0.7996   0.01553   0.00879  -0.0015   0.9986   0.0165
  -7.250  -0.7692   0.01484   0.00805  -0.0026   0.9923   0.0171
  -7.000  -0.7388   0.01418   0.00735  -0.0037   0.9848   0.0180
  -6.750  -0.7083   0.01369   0.00683  -0.0047   0.9760   0.0190
  -6.500  -0.6777   0.01325   0.00636  -0.0057   0.9659   0.0201
  -6.250  -0.6474   0.01285   0.00590  -0.0065   0.9545   0.0214
  -6.000  -0.6184   0.01244   0.00544  -0.0070   0.9415   0.0231
  -5.750  -0.5912   0.01207   0.00506  -0.0071   0.9266   0.0258
  -5.500  -0.5650   0.01180   0.00473  -0.0069   0.9112   0.0288
  -5.250  -0.5402   0.01148   0.00438  -0.0064   0.8956   0.0339
  -5.000  -0.5150   0.01123   0.00409  -0.0060   0.8809   0.0395
  -4.750  -0.4899   0.01098   0.00381  -0.0055   0.8670   0.0479
  -4.500  -0.4649   0.01071   0.00354  -0.0051   0.8538   0.0605
  -4.250  -0.4402   0.01040   0.00327  -0.0046   0.8415   0.0825
  -4.000  -0.4162   0.00996   0.00298  -0.0042   0.8295   0.1252
  -3.750  -0.3934   0.00936   0.00266  -0.0036   0.8183   0.1996
  -3.250  -0.3504   0.00793   0.00202  -0.0020   0.7979   0.4120
  -3.000  -0.3260   0.00760   0.00189  -0.0015   0.7881   0.4797
  -2.750  -0.3004   0.00742   0.00180  -0.0011   0.7790   0.5198
  -2.500  -0.2741   0.00729   0.00172  -0.0008   0.7701   0.5503
  -2.250  -0.2479   0.00717   0.00167  -0.0005   0.7618   0.5829
  -2.000  -0.2217   0.00707   0.00164  -0.0002   0.7530   0.6124
  -1.500  -0.1672   0.00700   0.00156   0.0001   0.7364   0.6437
  -1.250  -0.1395   0.00696   0.00153   0.0001   0.7285   0.6534
  -1.000  -0.1117   0.00696   0.00148   0.0001   0.7210   0.6610
  -0.750  -0.0837   0.00693   0.00146   0.0001   0.7130   0.6680
  -0.250  -0.0279   0.00692   0.00143   0.0000   0.6973   0.6828
   0.000   0.0000   0.00694   0.00142   0.0000   0.6903   0.6903
   0.250   0.0280   0.00692   0.00143   0.0000   0.6828   0.6973
   0.750   0.0838   0.00693   0.00146  -0.0001   0.6679   0.7129
   1.000   0.1117   0.00696   0.00148  -0.0001   0.6610   0.7210
   1.250   0.1396   0.00696   0.00153  -0.0001   0.6534   0.7285
   1.500   0.1673   0.00700   0.00156  -0.0001   0.6437   0.7364
   2.000   0.2217   0.00707   0.00164   0.0002   0.6124   0.7531
   2.250   0.2479   0.00717   0.00167   0.0005   0.5828   0.7618
   2.500   0.2741   0.00729   0.00172   0.0008   0.5504   0.7701
   2.750   0.3005   0.00742   0.00180   0.0011   0.5199   0.7790
   3.000   0.3261   0.00760   0.00189   0.0015   0.4796   0.7881
   3.250   0.3504   0.00793   0.00202   0.0020   0.4117   0.7978
   3.500   0.3719   0.00862   0.00230   0.0028   0.3036   0.8080
   3.750   0.3935   0.00936   0.00266   0.0036   0.1998   0.8183
   4.000   0.4162   0.00996   0.00298   0.0042   0.1251   0.8295
   4.250   0.4402   0.01040   0.00327   0.0046   0.0822   0.8415
   4.500   0.4649   0.01071   0.00354   0.0051   0.0604   0.8538
   4.750   0.4900   0.01098   0.00381   0.0055   0.0479   0.8669
   5.000   0.5151   0.01123   0.00409   0.0060   0.0395   0.8808
   5.250   0.5402   0.01148   0.00438   0.0064   0.0339   0.8957
   5.500   0.5651   0.01180   0.00473   0.0069   0.0288   0.9113
   5.750   0.5913   0.01207   0.00506   0.0071   0.0259   0.9266
   6.000   0.6184   0.01244   0.00544   0.0070   0.0231   0.9414
   6.250   0.6474   0.01285   0.00590   0.0065   0.0214   0.9545
   6.500   0.6778   0.01325   0.00636   0.0057   0.0201   0.9659
   6.750   0.7084   0.01369   0.00683   0.0047   0.0190   0.9760
   7.000   0.7387   0.01418   0.00735   0.0037   0.0180   0.9849
   7.250   0.7692   0.01484   0.00805   0.0026   0.0171   0.9922
   7.750   0.8210   0.01604   0.00936   0.0023   0.0161   1.0000
   8.000   0.8400   0.01654   0.00991   0.0037   0.0156   1.0000
   8.250   0.8594   0.01707   0.01049   0.0050   0.0151   1.0000
   8.500   0.8789   0.01766   0.01114   0.0061   0.0147   1.0000
   8.750   0.8985   0.01829   0.01183   0.0073   0.0143   1.0000
   9.000   0.9181   0.01894   0.01253   0.0083   0.0140   1.0000
   9.250   0.9375   0.01964   0.01328   0.0094   0.0137   1.0000
   9.500   0.9564   0.02040   0.01410   0.0104   0.0134   1.0000
   9.750   0.9741   0.02131   0.01507   0.0116   0.0131   1.0000
  10.000   0.9890   0.02267   0.01653   0.0131   0.0127   1.0000
  10.250   1.0078   0.02343   0.01741   0.0140   0.0125   1.0000
  10.500   1.0256   0.02428   0.01838   0.0151   0.0122   1.0000
  10.750   1.0421   0.02527   0.01950   0.0163   0.0119   1.0000
  11.000   1.0569   0.02639   0.02076   0.0176   0.0117   1.0000
  11.250   1.0693   0.02755   0.02207   0.0192   0.0114   1.0000
  11.500   1.0801   0.02879   0.02345   0.0210   0.0112   1.0000
  11.750   1.0894   0.03011   0.02493   0.0227   0.0110   1.0000
  12.000   1.0975   0.03152   0.02648   0.0243   0.0108   1.0000
  12.250   1.1045   0.03301   0.02810   0.0257   0.0106   1.0000
  12.500   1.1107   0.03454   0.02976   0.0269   0.0104   1.0000
  12.750   1.1163   0.03617   0.03150   0.0279   0.0102   1.0000
  13.000   1.1210   0.03791   0.03335   0.0286   0.0101   1.0000
  13.250   1.1243   0.03989   0.03544   0.0291   0.0099   1.0000
  13.500   1.1252   0.04224   0.03790   0.0293   0.0098   1.0000
  13.750   1.1219   0.04519   0.04099   0.0292   0.0096   1.0000
  14.000   1.1129   0.04901   0.04499   0.0287   0.0095   1.0000
  14.250   1.0976   0.05389   0.05008   0.0274   0.0094   1.0000
  14.500   1.0870   0.05848   0.05486   0.0257   0.0093   1.0000
  14.750   1.0722   0.06401   0.06059   0.0231   0.0093   1.0000
  15.000   1.0535   0.07056   0.06733   0.0196   0.0093   1.0000
  15.250   1.0303   0.07857   0.07554   0.0149   0.0093   1.0000
  15.500   1.0012   0.08871   0.08587   0.0086   0.0093   1.0000
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