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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 100,000
Max Cl/Cd: 48.88 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2408-il-100000-n5.txt
Download as CSV file: xf-naca2408-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5343   0.09125   0.08624  -0.0164   1.0000   0.0281
  -8.750  -0.5388   0.08566   0.08072  -0.0199   1.0000   0.0277
  -8.500  -0.5469   0.07927   0.07442  -0.0247   1.0000   0.0271
  -8.000  -0.5624   0.05876   0.05368  -0.0421   1.0000   0.0256
  -7.500  -0.5629   0.04670   0.04104  -0.0461   1.0000   0.0259
  -7.250  -0.5531   0.04368   0.03788  -0.0461   1.0000   0.0269
  -7.000  -0.5388   0.04185   0.03593  -0.0458   1.0000   0.0286
  -6.750  -0.5266   0.03828   0.03197  -0.0455   1.0000   0.0303
  -6.500  -0.5133   0.03408   0.02720  -0.0449   1.0000   0.0316
  -6.250  -0.4969   0.03039   0.02287  -0.0440   1.0000   0.0331
  -6.000  -0.4774   0.02773   0.01955  -0.0430   1.0000   0.0357
  -5.750  -0.4577   0.02606   0.01779  -0.0423   1.0000   0.0386
  -5.500  -0.4361   0.02438   0.01581  -0.0414   1.0000   0.0413
  -5.250  -0.4134   0.02306   0.01407  -0.0405   1.0000   0.0458
  -5.000  -0.3913   0.02157   0.01248  -0.0397   1.0000   0.0495
  -4.750  -0.3685   0.02062   0.01142  -0.0389   1.0000   0.0540
  -4.500  -0.3450   0.01984   0.01036  -0.0381   1.0000   0.0591
  -4.250  -0.3221   0.01876   0.00930  -0.0374   1.0000   0.0629
  -4.000  -0.2988   0.01815   0.00860  -0.0367   1.0000   0.0691
  -3.750  -0.2751   0.01745   0.00782  -0.0360   1.0000   0.0745
  -3.500  -0.2514   0.01682   0.00718  -0.0354   1.0000   0.0804
  -3.250  -0.2273   0.01626   0.00659  -0.0349   1.0000   0.0889
  -3.000  -0.2030   0.01576   0.00609  -0.0345   1.0000   0.1032
  -2.750  -0.1784   0.01529   0.00574  -0.0342   1.0000   0.1311
  -2.500  -0.1493   0.01479   0.00549  -0.0350   0.9980   0.1863
  -2.250  -0.1118   0.01430   0.00527  -0.0374   0.9920   0.2630
  -2.000  -0.0751   0.01361   0.00515  -0.0398   0.9863   0.3996
  -1.750  -0.0436   0.01272   0.00515  -0.0405   0.9797   0.6179
  -1.500  -0.0138   0.01215   0.00519  -0.0397   0.9736   0.8226
  -1.250   0.0394   0.01197   0.00501  -0.0444   0.9678   1.0000
  -1.000   0.0781   0.01199   0.00485  -0.0468   0.9590   1.0000
  -0.750   0.1186   0.01200   0.00471  -0.0495   0.9511   1.0000
  -0.500   0.1534   0.01200   0.00460  -0.0510   0.9397   1.0000
  -0.250   0.1881   0.01200   0.00450  -0.0523   0.9283   1.0000
   0.000   0.2222   0.01198   0.00442  -0.0535   0.9164   1.0000
   0.250   0.2558   0.01197   0.00434  -0.0545   0.9039   1.0000
   0.500   0.2882   0.01195   0.00428  -0.0553   0.8903   1.0000
   0.750   0.3191   0.01195   0.00424  -0.0557   0.8753   1.0000
   1.000   0.3493   0.01195   0.00422  -0.0558   0.8592   1.0000
   1.250   0.3788   0.01195   0.00421  -0.0558   0.8423   1.0000
   1.500   0.4081   0.01197   0.00420  -0.0557   0.8247   1.0000
   1.750   0.4362   0.01200   0.00423  -0.0554   0.8056   1.0000
   2.000   0.4636   0.01207   0.00428  -0.0549   0.7850   1.0000
   2.250   0.4912   0.01214   0.00432  -0.0544   0.7643   1.0000
   2.500   0.5176   0.01225   0.00444  -0.0538   0.7412   1.0000
   2.750   0.5441   0.01238   0.00455  -0.0531   0.7179   1.0000
   3.000   0.5700   0.01253   0.00466  -0.0523   0.6914   1.0000
   3.250   0.5945   0.01272   0.00478  -0.0511   0.6547   1.0000
   3.500   0.6182   0.01297   0.00488  -0.0498   0.6110   1.0000
   3.750   0.6413   0.01329   0.00501  -0.0485   0.5629   1.0000
   4.000   0.6647   0.01366   0.00523  -0.0474   0.5180   1.0000
   4.250   0.6876   0.01408   0.00551  -0.0463   0.4664   1.0000
   4.500   0.7107   0.01454   0.00583  -0.0453   0.4171   1.0000
   4.750   0.7326   0.01513   0.00620  -0.0443   0.3511   1.0000
   5.000   0.7530   0.01599   0.00670  -0.0431   0.2653   1.0000
   5.250   0.7714   0.01727   0.00742  -0.0420   0.1632   1.0000
   5.500   0.7902   0.01862   0.00833  -0.0409   0.0962   1.0000
   5.750   0.8112   0.01965   0.00927  -0.0399   0.0755   1.0000
   6.000   0.8330   0.02054   0.01024  -0.0389   0.0667   1.0000
   6.250   0.8535   0.02156   0.01132  -0.0378   0.0612   1.0000
   6.500   0.8744   0.02251   0.01242  -0.0367   0.0572   1.0000
   6.750   0.8953   0.02345   0.01345  -0.0357   0.0521   1.0000
   7.000   0.9136   0.02481   0.01479  -0.0344   0.0487   1.0000
   7.250   0.9346   0.02597   0.01615  -0.0333   0.0455   1.0000
   7.500   0.9551   0.02718   0.01750  -0.0323   0.0414   1.0000
   7.750   0.9745   0.02888   0.01922  -0.0312   0.0387   1.0000
   8.000   0.9951   0.03080   0.02133  -0.0302   0.0358   1.0000
   8.250   1.0157   0.03259   0.02341  -0.0291   0.0329   1.0000
   8.500   1.0352   0.03471   0.02578  -0.0280   0.0308   1.0000
   8.750   1.0523   0.03676   0.02797  -0.0270   0.0286   1.0000
   9.000   1.0659   0.04003   0.03148  -0.0257   0.0266   1.0000
   9.250   1.0784   0.04265   0.03461  -0.0239   0.0255   1.0000
   9.500   1.0863   0.04591   0.03837  -0.0219   0.0247   1.0000
   9.750   1.0894   0.04939   0.04240  -0.0197   0.0239   1.0000
  10.000   1.0880   0.05289   0.04632  -0.0174   0.0231   1.0000
  10.250   1.0824   0.05635   0.05015  -0.0152   0.0223   1.0000
  10.500   1.0712   0.05967   0.05375  -0.0128   0.0218   1.0000
  10.750   1.0561   0.06330   0.05764  -0.0110   0.0215   1.0000
  11.000   1.0376   0.06767   0.06224  -0.0106   0.0214   1.0000
  11.250   1.0156   0.07314   0.06795  -0.0122   0.0215   1.0000
  11.500   0.9902   0.08024   0.07526  -0.0160   0.0220   1.0000
  11.750   0.9625   0.08936   0.08450  -0.0224   0.0227   1.0000
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