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NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 200,000
Max Cl/Cd: 43.83 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001264-il-200000.txt
Download as CSV file: xf-naca001264-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5040   0.10445   0.10068  -0.0291   1.0000   0.0915
 -11.500  -0.8654   0.06388   0.05926  -0.0461   1.0000   0.0532
 -11.250  -0.8838   0.06002   0.05527  -0.0434   1.0000   0.0527
 -11.000  -0.9036   0.05659   0.05169  -0.0394   1.0000   0.0522
 -10.750  -0.9206   0.05290   0.04777  -0.0353   1.0000   0.0516
 -10.500  -0.9351   0.04923   0.04381  -0.0309   1.0000   0.0511
 -10.250  -0.9460   0.04579   0.04006  -0.0264   1.0000   0.0509
 -10.000  -0.9517   0.04291   0.03686  -0.0220   1.0000   0.0512
  -9.750  -0.9536   0.04041   0.03403  -0.0178   1.0000   0.0518
  -9.500  -0.9523   0.03811   0.03139  -0.0139   1.0000   0.0525
  -9.250  -0.9475   0.03600   0.02893  -0.0103   1.0000   0.0530
  -9.000  -0.9402   0.03414   0.02676  -0.0069   1.0000   0.0535
  -8.750  -0.9313   0.03293   0.02524  -0.0036   1.0000   0.0541
  -8.500  -0.9169   0.02995   0.02212  -0.0020   1.0000   0.0555
  -8.250  -0.9009   0.02870   0.02082  -0.0002   1.0000   0.0569
  -8.000  -0.8846   0.02754   0.01955   0.0017   1.0000   0.0580
  -7.750  -0.8673   0.02639   0.01826   0.0036   1.0000   0.0592
  -7.500  -0.8496   0.02536   0.01711   0.0054   1.0000   0.0607
  -7.250  -0.8318   0.02450   0.01610   0.0072   1.0000   0.0624
  -7.000  -0.8138   0.02379   0.01521   0.0090   1.0000   0.0637
  -6.750  -0.7929   0.02233   0.01370   0.0101   1.0000   0.0654
  -6.500  -0.7739   0.02137   0.01278   0.0116   1.0000   0.0673
  -6.250  -0.7557   0.02070   0.01211   0.0132   1.0000   0.0696
  -6.000  -0.7374   0.02013   0.01150   0.0149   1.0000   0.0725
  -5.750  -0.7187   0.01965   0.01093   0.0165   1.0000   0.0751
  -5.500  -0.7018   0.01867   0.01002   0.0183   1.0000   0.0786
  -5.250  -0.6844   0.01811   0.00950   0.0201   1.0000   0.0830
  -5.000  -0.6662   0.01767   0.00899   0.0218   1.0000   0.0884
  -4.750  -0.6499   0.01696   0.00839   0.0236   1.0000   0.0976
  -4.500  -0.6328   0.01636   0.00787   0.0253   1.0000   0.1119
  -4.250  -0.6156   0.01571   0.00740   0.0270   1.0000   0.1364
  -4.000  -0.5980   0.01507   0.00702   0.0284   1.0000   0.1791
  -3.750  -0.5810   0.01431   0.00668   0.0298   1.0000   0.2530
  -3.500  -0.5610   0.01312   0.00635   0.0303   0.9986   0.4127
  -3.250  -0.5339   0.01218   0.00637   0.0301   0.9954   0.6056
  -3.000  -0.5025   0.01201   0.00662   0.0297   0.9918   0.7082
  -2.750  -0.4705   0.01211   0.00692   0.0293   0.9874   0.7720
  -2.500  -0.4354   0.01241   0.00731   0.0284   0.9837   0.8177
  -2.250  -0.4047   0.01266   0.00756   0.0283   0.9784   0.8462
  -2.000  -0.3698   0.01297   0.00785   0.0273   0.9737   0.8651
  -1.750  -0.3309   0.01333   0.00816   0.0254   0.9705   0.8815
  -1.500  -0.3005   0.01366   0.00848   0.0254   0.9644   0.8976
  -1.250  -0.2615   0.01417   0.00895   0.0240   0.9605   0.9134
  -1.000  -0.2164   0.01465   0.00939   0.0211   0.9579   0.9264
  -0.750  -0.1566   0.01530   0.01001   0.0153   0.9577   0.9351
  -0.500  -0.1006   0.01564   0.01031   0.0097   0.9566   0.9425
  -0.250  -0.0460   0.01576   0.01042   0.0040   0.9543   0.9450
   0.000   0.0000   0.01579   0.01045   0.0000   0.9491   0.9491
   0.250   0.0460   0.01576   0.01042  -0.0040   0.9450   0.9543
   0.500   0.1006   0.01564   0.01031  -0.0097   0.9425   0.9566
   0.750   0.1566   0.01530   0.01001  -0.0153   0.9351   0.9577
   1.000   0.2165   0.01465   0.00939  -0.0211   0.9264   0.9579
   1.250   0.2614   0.01417   0.00895  -0.0240   0.9134   0.9605
   1.500   0.3004   0.01366   0.00847  -0.0254   0.8976   0.9645
   1.750   0.3308   0.01333   0.00816  -0.0254   0.8815   0.9705
   2.000   0.3697   0.01296   0.00784  -0.0273   0.8651   0.9738
   2.250   0.4046   0.01266   0.00756  -0.0283   0.8462   0.9785
   2.500   0.4354   0.01241   0.00731  -0.0284   0.8178   0.9837
   2.750   0.4704   0.01211   0.00692  -0.0293   0.7720   0.9874
   3.000   0.5024   0.01201   0.00662  -0.0297   0.7081   0.9918
   3.250   0.5339   0.01218   0.00637  -0.0301   0.6056   0.9954
   3.500   0.5610   0.01311   0.00635  -0.0303   0.4134   0.9987
   3.750   0.5809   0.01430   0.00667  -0.0298   0.2533   1.0000
   4.000   0.5979   0.01507   0.00701  -0.0284   0.1792   1.0000
   4.250   0.6155   0.01571   0.00740  -0.0269   0.1365   1.0000
   4.500   0.6327   0.01635   0.00787  -0.0253   0.1119   1.0000
   4.750   0.6498   0.01696   0.00839  -0.0236   0.0976   1.0000
   5.000   0.6661   0.01766   0.00898  -0.0218   0.0884   1.0000
   5.250   0.6843   0.01811   0.00949  -0.0201   0.0830   1.0000
   5.500   0.7017   0.01866   0.01002  -0.0183   0.0786   1.0000
   5.750   0.7186   0.01965   0.01092  -0.0165   0.0751   1.0000
   6.000   0.7373   0.02013   0.01149  -0.0148   0.0725   1.0000
   6.250   0.7556   0.02070   0.01211  -0.0132   0.0696   1.0000
   6.500   0.7738   0.02136   0.01277  -0.0115   0.0673   1.0000
   6.750   0.7928   0.02232   0.01370  -0.0101   0.0654   1.0000
   7.000   0.8137   0.02378   0.01521  -0.0090   0.0637   1.0000
   7.250   0.8317   0.02450   0.01610  -0.0072   0.0624   1.0000
   7.500   0.8495   0.02535   0.01710  -0.0053   0.0607   1.0000
   7.750   0.8672   0.02638   0.01826  -0.0035   0.0592   1.0000
   8.000   0.8845   0.02754   0.01954  -0.0017   0.0581   1.0000
   8.250   0.9008   0.02870   0.02082   0.0002   0.0569   1.0000
   8.500   0.9168   0.02995   0.02212   0.0020   0.0555   1.0000
   8.750   0.9312   0.03294   0.02524   0.0036   0.0541   1.0000
   9.000   0.9401   0.03413   0.02675   0.0069   0.0535   1.0000
   9.250   0.9475   0.03599   0.02893   0.0103   0.0530   1.0000
   9.500   0.9522   0.03811   0.03138   0.0139   0.0525   1.0000
   9.750   0.9536   0.04040   0.03402   0.0178   0.0518   1.0000
  10.000   0.9517   0.04291   0.03685   0.0220   0.0512   1.0000
  10.250   0.9461   0.04579   0.04006   0.0264   0.0509   1.0000
  10.500   0.9353   0.04923   0.04382   0.0309   0.0511   1.0000
  10.750   0.9208   0.05292   0.04778   0.0352   0.0516   1.0000
  11.000   0.9039   0.05662   0.05171   0.0393   0.0522   1.0000
  11.250   0.8840   0.06006   0.05531   0.0433   0.0527   1.0000
  11.500   0.8659   0.06394   0.05932   0.0459   0.0532   1.0000
  11.750   0.7323   0.06051   0.05639   0.0535   0.0559   1.0000
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