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NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il)
Reynolds number: 100,000
Max Cl/Cd: 49.91 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001264a08cli02-il-100000.txt
Download as CSV file: xf-naca001264a08cli02-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64 a=0.8 c(li)=0.2                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4149   0.09407   0.08947  -0.0416   1.0000   0.0969
  -9.500  -0.3982   0.09145   0.08686  -0.0378   1.0000   0.1049
  -9.250  -0.4169   0.08766   0.08314  -0.0390   1.0000   0.1081
  -9.000  -0.4402   0.08355   0.07911  -0.0405   1.0000   0.1088
  -8.750  -0.4626   0.07948   0.07511  -0.0412   1.0000   0.1089
  -8.500  -0.4878   0.07623   0.07189  -0.0397   1.0000   0.1089
  -8.250  -0.5123   0.07368   0.06937  -0.0363   1.0000   0.1088
  -8.000  -0.5386   0.07127   0.06697  -0.0323   1.0000   0.1089
  -7.750  -0.5661   0.06876   0.06441  -0.0286   1.0000   0.1093
  -7.500  -0.5928   0.06638   0.06190  -0.0246   1.0000   0.1097
  -7.250  -0.6323   0.07043   0.06556  -0.0223   1.0000   0.1078
  -7.000  -0.6351   0.06758   0.06273  -0.0194   1.0000   0.1149
  -6.750  -0.6619   0.06819   0.06270  -0.0140   1.0000   0.1232
  -6.500  -0.6419   0.06297   0.05796  -0.0133   1.0000   0.1335
  -6.250  -0.6432   0.06010   0.05504  -0.0105   1.0000   0.1426
  -6.000  -0.6449   0.05754   0.05236  -0.0075   1.0000   0.1548
  -5.750  -0.6427   0.05503   0.04980  -0.0047   1.0000   0.1691
  -5.500  -0.6384   0.05277   0.04750  -0.0018   1.0000   0.1871
  -5.250  -0.6347   0.05072   0.04548   0.0013   1.0000   0.2136
  -4.250  -0.6217   0.04419   0.03952   0.0194   1.0000   0.3958
  -4.000  -0.6166   0.04280   0.03844   0.0268   1.0000   0.4535
  -3.500  -0.4984   0.03178   0.02281   0.0149   1.0000   0.1107
  -3.250  -0.4703   0.02938   0.02001   0.0162   1.0000   0.0964
  -3.000  -0.4424   0.02767   0.01789   0.0176   1.0000   0.0845
  -2.750  -0.4153   0.02589   0.01598   0.0183   1.0000   0.0781
  -2.500  -0.3907   0.02547   0.01522   0.0198   1.0000   0.0731
  -2.250  -0.3657   0.02438   0.01411   0.0206   1.0000   0.0716
  -2.000  -0.3424   0.02368   0.01335   0.0215   1.0000   0.0728
  -1.750  -0.3199   0.02264   0.01240   0.0224   1.0000   0.0741
  -1.500  -0.2991   0.02206   0.01182   0.0237   1.0000   0.0746
  -1.250  -0.2784   0.02163   0.01133   0.0248   1.0000   0.0762
  -1.000  -0.2571   0.02136   0.01096   0.0258   1.0000   0.0807
  -0.750  -0.2350   0.02117   0.01075   0.0266   1.0000   0.0892
  -0.500  -0.0702   0.02017   0.01293   0.0008   1.0000   1.0000
  -0.250  -0.0569   0.02042   0.01302   0.0029   1.0000   1.0000
   0.000  -0.0433   0.02070   0.01315   0.0048   1.0000   1.0000
   0.250  -0.0098   0.02114   0.01343   0.0027   0.9956   1.0000
   0.500   0.0307   0.02161   0.01375  -0.0009   0.9884   1.0000
   0.750   0.0714   0.02213   0.01416  -0.0045   0.9813   1.0000
   1.000   0.1098   0.02257   0.01452  -0.0076   0.9732   1.0000
   1.250   0.1457   0.02298   0.01489  -0.0101   0.9646   1.0000
   1.500   0.1889   0.02347   0.01535  -0.0140   0.9571   1.0000
   1.750   0.2208   0.02378   0.01567  -0.0156   0.9466   1.0000
   2.000   0.2591   0.02415   0.01604  -0.0184   0.9371   1.0000
   2.250   0.3062   0.02443   0.01637  -0.0227   0.9281   1.0000
   2.500   0.3570   0.02436   0.01639  -0.0273   0.9139   1.0000
   2.750   0.4217   0.02385   0.01599  -0.0340   0.8986   1.0000
   3.000   0.4692   0.02349   0.01577  -0.0374   0.8849   1.0000
   3.250   0.5170   0.02302   0.01544  -0.0408   0.8715   1.0000
   3.500   0.5917   0.02146   0.01412  -0.0481   0.8562   1.0000
   3.750   0.6512   0.01980   0.01270  -0.0521   0.8398   1.0000
   4.000   0.6789   0.01907   0.01213  -0.0507   0.8188   1.0000
   4.250   0.7193   0.01787   0.01111  -0.0512   0.7975   1.0000
   4.500   0.7466   0.01690   0.01027  -0.0490   0.7604   1.0000
   4.750   0.7751   0.01599   0.00928  -0.0467   0.6914   1.0000
   5.000   0.7951   0.01593   0.00865  -0.0433   0.5514   1.0000
   5.250   0.7990   0.01728   0.00893  -0.0382   0.3813   1.0000
   5.500   0.8004   0.01895   0.00977  -0.0335   0.2673   1.0000
   5.750   0.8069   0.02047   0.01076  -0.0298   0.2043   1.0000
   6.000   0.8169   0.02184   0.01180  -0.0266   0.1653   1.0000
   6.250   0.8306   0.02306   0.01284  -0.0241   0.1398   1.0000
   6.500   0.8478   0.02426   0.01392  -0.0222   0.1246   1.0000
   6.750   0.8701   0.02561   0.01527  -0.0212   0.1151   1.0000
   7.000   0.8962   0.02717   0.01668  -0.0211   0.1081   1.0000
   7.250   0.9228   0.02868   0.01839  -0.0207   0.1037   1.0000
   7.500   0.9467   0.03008   0.01996  -0.0200   0.0989   1.0000
   7.750   0.9739   0.03226   0.02207  -0.0204   0.0941   1.0000
   8.000   0.9940   0.03400   0.02419  -0.0188   0.0922   1.0000
   8.250   1.0125   0.03606   0.02666  -0.0170   0.0906   1.0000
   8.500   1.0277   0.03831   0.02932  -0.0147   0.0889   1.0000
   8.750   1.0405   0.04036   0.03169  -0.0122   0.0861   1.0000
   9.000   1.0548   0.04252   0.03403  -0.0103   0.0837   1.0000
   9.250   1.0657   0.04536   0.03717  -0.0078   0.0826   1.0000
   9.500   1.0736   0.04939   0.04140  -0.0057   0.0808   1.0000
   9.750   1.0684   0.05226   0.04473  -0.0009   0.0798   1.0000
  10.000   1.0605   0.05511   0.04802   0.0041   0.0791   1.0000
  10.250   1.0527   0.05878   0.05202   0.0085   0.0792   1.0000
  10.500   1.0426   0.06262   0.05614   0.0127   0.0795   1.0000
  10.750   1.0296   0.06647   0.06023   0.0170   0.0797   1.0000
  11.000   1.0148   0.07042   0.06438   0.0210   0.0800   1.0000
  11.250   1.0000   0.07467   0.06876   0.0246   0.0803   1.0000
  11.500   0.7987   0.07027   0.06508   0.0402   0.0911   1.0000
  11.750   0.7742   0.07595   0.07082   0.0405   0.0923   1.0000
  12.000   0.7591   0.08169   0.07659   0.0404   0.0932   1.0000
  12.250   0.5856   0.12249   0.11732   0.0159   0.1777   1.0000
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