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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 50,000
Max Cl/Cd: 40.59 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e212-il-50000-n5.txt
Download as CSV file: xf-e212-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3307   0.12167   0.11450  -0.0354   1.0000   0.0534
 -11.250  -0.3323   0.11797   0.11084  -0.0362   1.0000   0.0522
 -10.750  -0.4431   0.11545   0.10787  -0.0375   1.0000   0.0474
 -10.500  -0.4411   0.11178   0.10424  -0.0380   1.0000   0.0470
 -10.250  -0.4403   0.10801   0.10053  -0.0387   1.0000   0.0466
 -10.000  -0.4410   0.10411   0.09667  -0.0395   1.0000   0.0463
  -9.750  -0.4434   0.10000   0.09263  -0.0404   1.0000   0.0460
  -9.500  -0.4473   0.09575   0.08846  -0.0415   1.0000   0.0457
  -9.250  -0.4530   0.09133   0.08413  -0.0427   1.0000   0.0453
  -9.000  -0.4611   0.08667   0.07958  -0.0440   1.0000   0.0449
  -8.750  -0.4726   0.08163   0.07465  -0.0456   1.0000   0.0445
  -8.500  -0.4890   0.07616   0.06932  -0.0473   1.0000   0.0440
  -8.250  -0.5107   0.07041   0.06365  -0.0499   1.0000   0.0433
  -8.000  -0.5304   0.06410   0.05733  -0.0542   1.0000   0.0427
  -7.750  -0.5442   0.05850   0.05155  -0.0570   1.0000   0.0423
  -7.500  -0.5498   0.05328   0.04604  -0.0591   1.0000   0.0423
  -7.250  -0.5469   0.04863   0.04101  -0.0607   1.0000   0.0425
  -7.000  -0.5372   0.04458   0.03650  -0.0619   1.0000   0.0435
  -6.750  -0.5224   0.04100   0.03240  -0.0628   1.0000   0.0451
  -6.500  -0.5037   0.03778   0.02854  -0.0634   1.0000   0.0471
  -6.250  -0.4846   0.03545   0.02605  -0.0633   1.0000   0.0494
  -6.000  -0.4639   0.03348   0.02386  -0.0630   1.0000   0.0516
  -5.750  -0.4420   0.03158   0.02169  -0.0626   1.0000   0.0546
  -5.500  -0.4193   0.02985   0.01961  -0.0620   1.0000   0.0588
  -5.250  -0.3971   0.02848   0.01825  -0.0619   1.0000   0.0663
  -5.000  -0.3734   0.02707   0.01674  -0.0619   1.0000   0.0779
  -4.750  -0.3482   0.02568   0.01537  -0.0623   1.0000   0.1009
  -4.500  -0.3223   0.02455   0.01445  -0.0633   1.0000   0.1478
  -4.250  -0.2971   0.02368   0.01369  -0.0638   1.0000   0.1991
  -4.000  -0.2718   0.02308   0.01316  -0.0641   1.0000   0.2455
  -3.750  -0.2470   0.02267   0.01278  -0.0642   1.0000   0.2898
  -3.500  -0.2227   0.02238   0.01253  -0.0640   1.0000   0.3307
  -3.250  -0.1987   0.02218   0.01234  -0.0637   1.0000   0.3699
  -3.000  -0.1754   0.02205   0.01220  -0.0632   1.0000   0.4076
  -2.750  -0.1524   0.02197   0.01211  -0.0627   1.0000   0.4445
  -2.500  -0.1303   0.02195   0.01211  -0.0619   1.0000   0.4790
  -2.250  -0.1086   0.02197   0.01213  -0.0611   0.9999   0.5133
  -2.000  -0.0722   0.02214   0.01228  -0.0630   0.9923   0.5542
  -1.750  -0.0366   0.02233   0.01249  -0.0646   0.9847   0.5925
  -1.500  -0.0029   0.02244   0.01256  -0.0659   0.9759   0.6305
  -1.250   0.0289   0.02253   0.01268  -0.0666   0.9668   0.6659
  -1.000   0.0608   0.02261   0.01278  -0.0673   0.9578   0.7025
  -0.750   0.0927   0.02266   0.01283  -0.0678   0.9486   0.7403
  -0.500   0.1190   0.02262   0.01283  -0.0673   0.9377   0.7773
  -0.250   0.1450   0.02254   0.01279  -0.0666   0.9269   0.8181
   0.000   0.1724   0.02239   0.01267  -0.0661   0.9168   0.8662
   0.250   0.2093   0.02213   0.01243  -0.0676   0.9065   0.9403
   0.500   0.2494   0.02207   0.01225  -0.0708   0.8941   1.0000
   0.750   0.2879   0.02219   0.01224  -0.0734   0.8829   1.0000
   1.000   0.3290   0.02228   0.01221  -0.0763   0.8731   1.0000
   1.250   0.3682   0.02233   0.01219  -0.0787   0.8622   1.0000
   1.750   0.4391   0.02243   0.01222  -0.0817   0.8375   1.0000
   2.000   0.4767   0.02240   0.01219  -0.0834   0.8258   1.0000
   2.250   0.5189   0.02227   0.01207  -0.0856   0.8154   1.0000
   2.500   0.5538   0.02225   0.01208  -0.0867   0.8015   1.0000
   2.750   0.5883   0.02221   0.01210  -0.0875   0.7870   1.0000
   3.000   0.6229   0.02216   0.01209  -0.0883   0.7720   1.0000
   3.250   0.6578   0.02209   0.01208  -0.0890   0.7564   1.0000
   3.500   0.6927   0.02200   0.01207  -0.0897   0.7400   1.0000
   3.750   0.7223   0.02208   0.01223  -0.0895   0.7204   1.0000
   4.000   0.7541   0.02210   0.01232  -0.0896   0.7007   1.0000
   4.250   0.7876   0.02207   0.01237  -0.0899   0.6806   1.0000
   4.500   0.8161   0.02222   0.01259  -0.0895   0.6575   1.0000
   4.750   0.8474   0.02229   0.01270  -0.0893   0.6342   1.0000
   5.000   0.8736   0.02254   0.01303  -0.0886   0.6079   1.0000
   5.250   0.9003   0.02280   0.01334  -0.0878   0.5809   1.0000
   5.500   0.9260   0.02312   0.01368  -0.0869   0.5529   1.0000
   5.750   0.9502   0.02351   0.01411  -0.0858   0.5234   1.0000
   6.000   0.9730   0.02397   0.01458  -0.0845   0.4929   1.0000
   6.250   0.9944   0.02451   0.01513  -0.0831   0.4612   1.0000
   6.500   1.0145   0.02513   0.01574  -0.0816   0.4288   1.0000
   6.750   1.0334   0.02583   0.01645  -0.0799   0.3960   1.0000
   7.000   1.0512   0.02662   0.01720  -0.0782   0.3634   1.0000
   7.250   1.0677   0.02750   0.01805  -0.0764   0.3311   1.0000
   7.500   1.0830   0.02849   0.01900  -0.0745   0.2989   1.0000
   7.750   1.0972   0.02959   0.02008  -0.0725   0.2673   1.0000
   8.000   1.1102   0.03081   0.02128  -0.0706   0.2374   1.0000
   8.250   1.1220   0.03215   0.02257  -0.0685   0.2097   1.0000
   8.500   1.1323   0.03360   0.02398  -0.0664   0.1841   1.0000
   8.750   1.1418   0.03516   0.02556  -0.0642   0.1603   1.0000
   9.000   1.1485   0.03691   0.02721  -0.0618   0.1400   1.0000
   9.250   1.1539   0.03874   0.02908  -0.0595   0.1182   1.0000
   9.500   1.1551   0.04074   0.03097  -0.0572   0.1003   1.0000
   9.750   1.1585   0.04288   0.03319  -0.0552   0.0836   1.0000
  10.000   1.1610   0.04526   0.03559  -0.0533   0.0722   1.0000
  10.250   1.1635   0.04776   0.03814  -0.0516   0.0638   1.0000
  10.500   1.1693   0.05036   0.04094  -0.0500   0.0569   1.0000
  10.750   1.1709   0.05301   0.04360  -0.0486   0.0525   1.0000
  11.000   1.1780   0.05579   0.04668  -0.0474   0.0481   1.0000
  11.250   1.1825   0.05865   0.04973  -0.0463   0.0451   1.0000
  11.500   1.1868   0.06159   0.05276  -0.0454   0.0432   1.0000
  11.750   1.1923   0.06488   0.05623  -0.0446   0.0417   1.0000
  12.000   1.1933   0.06877   0.06054  -0.0440   0.0405   1.0000
  12.250   1.1890   0.07308   0.06520  -0.0439   0.0396   1.0000
  12.500   1.1806   0.07784   0.07029  -0.0443   0.0389   1.0000
  12.750   1.1686   0.08317   0.07591  -0.0456   0.0384   1.0000
  13.000   1.1534   0.08921   0.08224  -0.0477   0.0382   1.0000
  13.250   1.1349   0.09616   0.08946  -0.0509   0.0382   1.0000
  13.500   1.1133   0.10427   0.09781  -0.0554   0.0385   1.0000
  13.750   1.0891   0.11369   0.10743  -0.0612   0.0390   1.0000
  14.000   1.0639   0.12446   0.11838  -0.0682   0.0397   1.0000
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