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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 100,000
Max Cl/Cd: 42.53 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212ma-il-100000.txt
Download as CSV file: xf-n64212ma-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3718   0.10186   0.09670  -0.0284   1.0000   0.0936
  -9.250  -0.3740   0.09860   0.09351  -0.0307   1.0000   0.0971
  -9.000  -0.4026   0.09474   0.08976  -0.0383   1.0000   0.0990
  -8.750  -0.3886   0.09077   0.08584  -0.0365   1.0000   0.1008
  -8.500  -0.3720   0.08820   0.08330  -0.0344   1.0000   0.1039
  -8.250  -0.3757   0.08495   0.08013  -0.0360   1.0000   0.1073
  -8.000  -0.3998   0.08116   0.07647  -0.0396   1.0000   0.1093
  -7.750  -0.4347   0.07896   0.07433  -0.0398   1.0000   0.1102
  -7.500  -0.4712   0.07813   0.07348  -0.0368   1.0000   0.1107
  -7.250  -0.5073   0.07796   0.07318  -0.0331   1.0000   0.1111
  -6.750  -0.4955   0.07104   0.06662  -0.0277   1.0000   0.1149
  -6.500  -0.5027   0.06924   0.06484  -0.0251   1.0000   0.1174
  -6.250  -0.5132   0.06740   0.06293  -0.0235   1.0000   0.1211
  -6.000  -0.5006   0.06316   0.05849  -0.0274   0.9946   0.1279
  -5.750  -0.4754   0.06038   0.05529  -0.0329   0.9857   0.1413
  -5.500  -0.4459   0.05631   0.05149  -0.0345   0.9813   0.1495
  -5.250  -0.4234   0.05302   0.04807  -0.0373   0.9735   0.1640
  -5.000  -0.3942   0.04984   0.04479  -0.0407   0.9674   0.1828
  -4.750  -0.3719   0.04714   0.04203  -0.0423   0.9588   0.2033
  -4.500  -0.3418   0.04421   0.03902  -0.0455   0.9522   0.2426
  -4.250  -0.3199   0.04169   0.03665  -0.0454   0.9428   0.2715
  -4.000  -0.2866   0.03886   0.03390  -0.0475   0.9361   0.3147
  -3.750  -0.2620   0.03771   0.03246  -0.0485   0.9257   0.3468
  -3.500  -0.2260   0.03432   0.02943  -0.0493   0.9194   0.3799
  -3.250  -0.1233   0.01736   0.01117  -0.0611   0.8995   0.2464
  -3.000  -0.0873   0.03031   0.02221  -0.0595   0.9045   0.1222
  -2.750  -0.0375   0.02823   0.01973  -0.0620   0.8991   0.1086
  -2.500  -0.0058   0.02697   0.01836  -0.0622   0.8907   0.1069
  -2.250   0.0272   0.02584   0.01710  -0.0625   0.8831   0.1049
  -2.000   0.0673   0.02470   0.01579  -0.0636   0.8782   0.1020
  -1.750   0.0944   0.02404   0.01508  -0.0629   0.8697   0.1014
  -1.500   0.1263   0.02313   0.01421  -0.0628   0.8607   0.1020
  -1.250   0.1653   0.02204   0.01323  -0.0635   0.8536   0.1064
  -1.000   0.1859   0.02158   0.01283  -0.0615   0.8403   0.1096
  -0.750   0.2199   0.02052   0.01183  -0.0609   0.8320   0.1131
  -0.500   0.2386   0.02013   0.01149  -0.0589   0.8183   0.1178
  -0.250   0.2700   0.01933   0.01065  -0.0583   0.8100   0.1290
   0.000   0.2916   0.01893   0.01031  -0.0568   0.7965   0.1472
   0.250   0.3069   0.01674   0.01012  -0.0533   0.7883   0.6856
   0.500   0.3074   0.01708   0.01087  -0.0449   0.7770   0.8208
   0.750   0.3148   0.01715   0.01098  -0.0372   0.7679   0.8806
   1.000   0.3362   0.01710   0.01090  -0.0328   0.7561   0.9266
   1.250   0.4713   0.01630   0.00986  -0.0483   0.7333   0.9778
   1.500   0.5134   0.01577   0.00921  -0.0506   0.7144   0.9860
   1.750   0.5528   0.01534   0.00868  -0.0526   0.6944   0.9946
   2.000   0.5826   0.01500   0.00828  -0.0531   0.6706   1.0000
   2.250   0.5963   0.01480   0.00804  -0.0506   0.6453   1.0000
   2.500   0.6089   0.01460   0.00772  -0.0477   0.6113   1.0000
   2.750   0.6175   0.01452   0.00744  -0.0441   0.5505   1.0000
   3.000   0.6141   0.01514   0.00711  -0.0385   0.3841   1.0000
   3.250   0.6091   0.01630   0.00756  -0.0336   0.3014   1.0000
   3.500   0.6133   0.01716   0.00803  -0.0301   0.2706   1.0000
   3.750   0.6281   0.01790   0.00852  -0.0282   0.2523   1.0000
   4.000   0.6489   0.01856   0.00899  -0.0273   0.2404   1.0000
   4.250   0.6721   0.01924   0.00946  -0.0268   0.2321   1.0000
   4.500   0.6977   0.01990   0.00998  -0.0265   0.2261   1.0000
   4.750   0.7242   0.02050   0.01052  -0.0264   0.2211   1.0000
   5.000   0.7512   0.02115   0.01105  -0.0264   0.2171   1.0000
   5.250   0.7790   0.02192   0.01167  -0.0266   0.2139   1.0000
   5.500   0.8074   0.02275   0.01241  -0.0268   0.2116   1.0000
   5.750   0.8352   0.02344   0.01315  -0.0269   0.2098   1.0000
   6.000   0.8628   0.02416   0.01391  -0.0270   0.2077   1.0000
   6.250   0.8897   0.02488   0.01467  -0.0270   0.2051   1.0000
   6.500   0.9161   0.02559   0.01539  -0.0270   0.2019   1.0000
   6.750   0.9427   0.02636   0.01607  -0.0271   0.1985   1.0000
   7.000   0.9695   0.02734   0.01700  -0.0272   0.1954   1.0000
   7.250   0.9937   0.02803   0.01786  -0.0269   0.1927   1.0000
   7.500   1.0183   0.02880   0.01876  -0.0266   0.1899   1.0000
   7.750   1.0428   0.02958   0.01963  -0.0264   0.1870   1.0000
   8.000   1.0677   0.03037   0.02042  -0.0262   0.1841   1.0000
   8.250   1.0945   0.03148   0.02144  -0.0265   0.1811   1.0000
   8.500   1.1150   0.03228   0.02252  -0.0257   0.1784   1.0000
   8.750   1.1361   0.03305   0.02347  -0.0250   0.1746   1.0000
   9.000   1.1590   0.03376   0.02423  -0.0246   0.1708   1.0000
   9.250   1.1846   0.03468   0.02504  -0.0247   0.1671   1.0000
   9.500   1.1999   0.03554   0.02628  -0.0234   0.1629   1.0000
   9.750   1.2211   0.03592   0.02666  -0.0227   0.1574   1.0000
  10.000   1.2382   0.03670   0.02758  -0.0217   0.1521   1.0000
  10.250   1.2574   0.03697   0.02787  -0.0208   0.1459   1.0000
  10.500   1.2695   0.03772   0.02881  -0.0191   0.1392   1.0000
  10.750   1.2841   0.03826   0.02938  -0.0177   0.1323   1.0000
  11.000   1.2982   0.03890   0.03001  -0.0163   0.1251   1.0000
  11.250   1.3122   0.03991   0.03099  -0.0150   0.1181   1.0000
  11.500   1.3297   0.04128   0.03227  -0.0142   0.1119   1.0000
  11.750   1.3379   0.04333   0.03451  -0.0125   0.1066   1.0000
  12.000   1.3423   0.04572   0.03714  -0.0106   0.1027   1.0000
  12.250   1.3618   0.04756   0.03893  -0.0103   0.0990   1.0000
  12.500   1.3485   0.05023   0.04202  -0.0067   0.0968   1.0000
  12.750   1.3768   0.05196   0.04360  -0.0074   0.0938   1.0000
  13.000   1.3508   0.05509   0.04719  -0.0033   0.0929   1.0000
  13.250   1.3274   0.05868   0.05115  -0.0006   0.0921   1.0000
  13.500   1.3031   0.06279   0.05559   0.0010   0.0914   1.0000
  13.750   1.2753   0.06765   0.06076   0.0016   0.0910   1.0000
  14.000   1.2366   0.07414   0.06757   0.0007   0.0910   1.0000
  14.250   1.1727   0.08470   0.07852  -0.0036   0.0919   1.0000
  14.500   1.0938   0.10065   0.09476  -0.0128   0.0935   1.0000
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