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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 50,000
Max Cl/Cd: 38.83 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e222-il-50000-n5.txt
Download as CSV file: xf-e222-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E222  (10.17%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4605   0.08991   0.08279  -0.0434   1.0000   0.0482
  -9.000  -0.4633   0.08595   0.07891  -0.0442   1.0000   0.0479
  -8.750  -0.4689   0.08176   0.07480  -0.0453   1.0000   0.0475
  -8.500  -0.4797   0.07702   0.07015  -0.0471   1.0000   0.0471
  -8.250  -0.4926   0.07248   0.06569  -0.0491   1.0000   0.0466
  -8.000  -0.5052   0.06784   0.06105  -0.0508   1.0000   0.0462
  -7.750  -0.5152   0.06343   0.05658  -0.0518   1.0000   0.0458
  -7.500  -0.5225   0.05906   0.05207  -0.0524   1.0000   0.0455
  -7.250  -0.5256   0.05476   0.04755  -0.0528   1.0000   0.0452
  -7.000  -0.5243   0.05057   0.04305  -0.0529   1.0000   0.0451
  -6.750  -0.5182   0.04660   0.03868  -0.0528   1.0000   0.0451
  -6.500  -0.5077   0.04297   0.03461  -0.0526   1.0000   0.0453
  -6.250  -0.4936   0.03969   0.03086  -0.0522   1.0000   0.0457
  -6.000  -0.4766   0.03682   0.02750  -0.0516   1.0000   0.0464
  -5.750  -0.4575   0.03442   0.02460  -0.0509   1.0000   0.0478
  -5.500  -0.4385   0.03241   0.02239  -0.0502   1.0000   0.0502
  -5.250  -0.4189   0.03092   0.02077  -0.0495   1.0000   0.0536
  -5.000  -0.3980   0.02940   0.01896  -0.0485   1.0000   0.0567
  -4.750  -0.3766   0.02797   0.01725  -0.0473   1.0000   0.0595
  -4.500  -0.3558   0.02665   0.01583  -0.0462   1.0000   0.0633
  -4.250  -0.3346   0.02555   0.01464  -0.0454   1.0000   0.0694
  -4.000  -0.3125   0.02446   0.01351  -0.0448   1.0000   0.0822
  -3.750  -0.2896   0.02325   0.01243  -0.0445   1.0000   0.1150
  -3.500  -0.2660   0.02200   0.01174  -0.0451   1.0000   0.2071
  -3.250  -0.2434   0.02123   0.01144  -0.0451   1.0000   0.3123
  -3.000  -0.2220   0.02079   0.01127  -0.0444   1.0000   0.3934
  -2.750  -0.2015   0.02052   0.01117  -0.0433   1.0000   0.4639
  -2.500  -0.1821   0.02035   0.01113  -0.0419   1.0000   0.5264
  -2.250  -0.1494   0.02033   0.01120  -0.0427   0.9922   0.5984
  -2.000  -0.1175   0.02038   0.01132  -0.0431   0.9838   0.6664
  -1.750  -0.0893   0.02039   0.01138  -0.0427   0.9743   0.7292
  -1.500  -0.0623   0.02038   0.01138  -0.0419   0.9647   0.7914
  -1.250  -0.0317   0.02036   0.01134  -0.0417   0.9558   0.8611
  -1.000   0.0162   0.02023   0.01110  -0.0455   0.9472   0.9522
  -0.750   0.0597   0.02024   0.01082  -0.0495   0.9365   1.0000
  -0.500   0.0990   0.02041   0.01073  -0.0525   0.9271   1.0000
  -0.250   0.1378   0.02057   0.01068  -0.0553   0.9171   1.0000
   0.000   0.1723   0.02071   0.01064  -0.0571   0.9057   1.0000
   0.250   0.2080   0.02086   0.01064  -0.0590   0.8948   1.0000
   0.500   0.2469   0.02097   0.01063  -0.0613   0.8850   1.0000
   0.750   0.2839   0.02106   0.01062  -0.0632   0.8743   1.0000
   1.000   0.3176   0.02117   0.01066  -0.0645   0.8622   1.0000
   1.250   0.3523   0.02125   0.01070  -0.0658   0.8505   1.0000
   1.500   0.3877   0.02131   0.01072  -0.0672   0.8389   1.0000
   1.750   0.4240   0.02131   0.01071  -0.0685   0.8276   1.0000
   2.000   0.4599   0.02129   0.01072  -0.0697   0.8158   1.0000
   2.250   0.4919   0.02133   0.01077  -0.0702   0.8020   1.0000
   2.500   0.5239   0.02136   0.01082  -0.0706   0.7880   1.0000
   2.750   0.5560   0.02137   0.01089  -0.0710   0.7735   1.0000
   3.000   0.5880   0.02136   0.01094  -0.0713   0.7585   1.0000
   3.250   0.6185   0.02140   0.01102  -0.0713   0.7423   1.0000
   3.500   0.6465   0.02149   0.01119  -0.0709   0.7244   1.0000
   3.750   0.6758   0.02155   0.01135  -0.0706   0.7063   1.0000
   4.000   0.7062   0.02157   0.01143  -0.0704   0.6879   1.0000
   4.250   0.7339   0.02169   0.01161  -0.0698   0.6676   1.0000
   4.500   0.7612   0.02181   0.01181  -0.0691   0.6462   1.0000
   4.750   0.7881   0.02197   0.01208  -0.0684   0.6238   1.0000
   5.000   0.8148   0.02215   0.01231  -0.0676   0.6003   1.0000
   5.250   0.8389   0.02242   0.01265  -0.0664   0.5747   1.0000
   5.500   0.8629   0.02272   0.01300  -0.0653   0.5479   1.0000
   5.750   0.8861   0.02306   0.01343  -0.0640   0.5198   1.0000
   6.000   0.9082   0.02346   0.01386  -0.0626   0.4903   1.0000
   6.250   0.9293   0.02393   0.01435  -0.0611   0.4595   1.0000
   6.500   0.9492   0.02448   0.01489  -0.0595   0.4277   1.0000
   6.750   0.9677   0.02512   0.01552  -0.0578   0.3947   1.0000
   7.000   0.9849   0.02586   0.01631  -0.0560   0.3610   1.0000
   7.250   1.0010   0.02670   0.01711  -0.0541   0.3276   1.0000
   7.500   1.0160   0.02765   0.01803  -0.0522   0.2948   1.0000
   7.750   1.0297   0.02873   0.01908  -0.0502   0.2620   1.0000
   8.000   1.0425   0.02993   0.02024  -0.0483   0.2315   1.0000
   8.250   1.0542   0.03125   0.02153  -0.0463   0.2032   1.0000
   8.500   1.0648   0.03271   0.02300  -0.0443   0.1772   1.0000
   8.750   1.0738   0.03431   0.02453  -0.0422   0.1545   1.0000
   9.000   1.0814   0.03599   0.02625  -0.0399   0.1329   1.0000
   9.250   1.0860   0.03787   0.02804  -0.0376   0.1143   1.0000
   9.500   1.0895   0.03982   0.03005  -0.0354   0.0952   1.0000
   9.750   1.0902   0.04191   0.03212  -0.0333   0.0794   1.0000
  10.000   1.0922   0.04423   0.03447  -0.0315   0.0672   1.0000
  10.250   1.0955   0.04675   0.03711  -0.0298   0.0583   1.0000
  10.500   1.0966   0.04939   0.03972  -0.0284   0.0529   1.0000
  10.750   1.1037   0.05204   0.04268  -0.0271   0.0472   1.0000
  11.000   1.1050   0.05477   0.04548  -0.0261   0.0435   1.0000
  11.250   1.1090   0.05777   0.04870  -0.0252   0.0408   1.0000
  11.500   1.1139   0.06111   0.05241  -0.0243   0.0386   1.0000
  11.750   1.1150   0.06475   0.05635  -0.0237   0.0372   1.0000
  12.000   1.1124   0.06869   0.06058  -0.0235   0.0362   1.0000
  12.250   1.1062   0.07307   0.06523  -0.0239   0.0355   1.0000
  12.500   1.0969   0.07792   0.07034  -0.0249   0.0350   1.0000
  12.750   1.0844   0.08342   0.07610  -0.0267   0.0347   1.0000
  13.000   1.0684   0.08975   0.08268  -0.0294   0.0347   1.0000
  13.250   1.0484   0.09727   0.09045  -0.0335   0.0349   1.0000
  13.500   1.0243   0.10638   0.09979  -0.0390   0.0354   1.0000
  13.750   0.9967   0.11744   0.11106  -0.0461   0.0362   1.0000
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