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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 100,000
Max Cl/Cd: 55.76 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e222-il-100000-n5.txt
Download as CSV file: xf-e222-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4573   0.09403   0.08885  -0.0392   1.0000   0.0279
  -9.750  -0.4596   0.09000   0.08487  -0.0402   1.0000   0.0276
  -9.500  -0.4636   0.08571   0.08064  -0.0415   1.0000   0.0273
  -9.250  -0.4703   0.08100   0.07600  -0.0431   1.0000   0.0271
  -9.000  -0.4797   0.07591   0.07099  -0.0451   1.0000   0.0268
  -8.750  -0.4940   0.06989   0.06505  -0.0478   1.0000   0.0264
  -8.500  -0.5205   0.06337   0.05859  -0.0516   1.0000   0.0261
  -8.250  -0.5393   0.05828   0.05341  -0.0537   1.0000   0.0258
  -8.000  -0.5543   0.05352   0.04849  -0.0543   1.0000   0.0256
  -7.750  -0.5628   0.04910   0.04381  -0.0543   1.0000   0.0254
  -7.500  -0.5651   0.04487   0.03925  -0.0540   1.0000   0.0253
  -7.250  -0.5616   0.04097   0.03494  -0.0535   1.0000   0.0252
  -7.000  -0.5528   0.03745   0.03098  -0.0529   1.0000   0.0253
  -6.750  -0.5399   0.03446   0.02754  -0.0522   1.0000   0.0257
  -6.500  -0.5237   0.03206   0.02465  -0.0515   1.0000   0.0267
  -6.250  -0.5052   0.03009   0.02220  -0.0508   1.0000   0.0277
  -6.000  -0.4856   0.02817   0.01995  -0.0500   1.0000   0.0282
  -5.750  -0.4654   0.02628   0.01784  -0.0493   1.0000   0.0287
  -5.500  -0.4342   0.02457   0.01595  -0.0507   0.9969   0.0294
  -5.250  -0.4008   0.02321   0.01445  -0.0523   0.9932   0.0304
  -5.000  -0.3677   0.02206   0.01314  -0.0538   0.9887   0.0316
  -4.750  -0.3330   0.02106   0.01200  -0.0555   0.9845   0.0335
  -4.500  -0.2999   0.02021   0.01098  -0.0569   0.9795   0.0361
  -4.250  -0.2659   0.01938   0.01010  -0.0587   0.9743   0.0417
  -4.000  -0.2300   0.01860   0.00924  -0.0606   0.9698   0.0510
  -3.750  -0.1983   0.01762   0.00840  -0.0618   0.9634   0.0844
  -3.500  -0.1627   0.01680   0.00794  -0.0640   0.9587   0.1662
  -3.250  -0.1320   0.01609   0.00772  -0.0653   0.9519   0.2713
  -3.000  -0.0979   0.01555   0.00756  -0.0670   0.9463   0.3740
  -2.750  -0.0660   0.01523   0.00740  -0.0679   0.9395   0.4365
  -2.500  -0.0323   0.01496   0.00723  -0.0690   0.9330   0.4927
  -2.250   0.0000   0.01474   0.00710  -0.0698   0.9263   0.5449
  -2.000   0.0324   0.01453   0.00697  -0.0704   0.9192   0.5950
  -1.750   0.0646   0.01434   0.00685  -0.0709   0.9125   0.6419
  -1.500   0.0961   0.01418   0.00675  -0.0712   0.9050   0.6855
  -1.250   0.1270   0.01403   0.00663  -0.0713   0.8974   0.7272
  -1.000   0.1573   0.01387   0.00652  -0.0711   0.8897   0.7663
  -0.750   0.1843   0.01375   0.00643  -0.0703   0.8802   0.8034
  -0.500   0.2162   0.01357   0.00625  -0.0704   0.8732   0.8402
  -0.250   0.2422   0.01344   0.00614  -0.0693   0.8623   0.8771
   0.000   0.2749   0.01329   0.00597  -0.0697   0.8527   0.9161
   0.250   0.3200   0.01309   0.00573  -0.0728   0.8449   0.9549
   0.500   0.3631   0.01295   0.00554  -0.0759   0.8333   1.0000
   0.750   0.3938   0.01292   0.00543  -0.0765   0.8207   1.0000
   1.000   0.4247   0.01290   0.00534  -0.0770   0.8078   1.0000
   1.250   0.4554   0.01289   0.00527  -0.0774   0.7941   1.0000
   1.500   0.4856   0.01291   0.00522  -0.0778   0.7797   1.0000
   1.750   0.5153   0.01294   0.00521  -0.0780   0.7645   1.0000
   2.000   0.5445   0.01299   0.00521  -0.0781   0.7486   1.0000
   2.250   0.5734   0.01306   0.00523  -0.0781   0.7320   1.0000
   2.500   0.6021   0.01315   0.00529  -0.0780   0.7150   1.0000
   2.750   0.6290   0.01327   0.00538  -0.0777   0.6961   1.0000
   3.000   0.6559   0.01341   0.00549  -0.0773   0.6766   1.0000
   3.250   0.6831   0.01357   0.00559  -0.0769   0.6572   1.0000
   3.500   0.7088   0.01375   0.00578  -0.0763   0.6359   1.0000
   3.750   0.7348   0.01396   0.00594  -0.0758   0.6145   1.0000
   4.000   0.7599   0.01419   0.00615  -0.0751   0.5915   1.0000
   4.250   0.7849   0.01444   0.00636  -0.0744   0.5679   1.0000
   4.500   0.8092   0.01473   0.00664  -0.0736   0.5428   1.0000
   4.750   0.8331   0.01504   0.00692  -0.0727   0.5164   1.0000
   5.000   0.8565   0.01538   0.00722  -0.0718   0.4891   1.0000
   5.250   0.8793   0.01577   0.00756  -0.0708   0.4607   1.0000
   5.500   0.9016   0.01619   0.00796  -0.0698   0.4311   1.0000
   5.750   0.9233   0.01666   0.00837  -0.0687   0.4005   1.0000
   6.000   0.9444   0.01718   0.00883  -0.0675   0.3692   1.0000
   6.250   0.9650   0.01774   0.00933  -0.0663   0.3370   1.0000
   6.500   0.9850   0.01836   0.00988  -0.0650   0.3041   1.0000
   6.750   1.0043   0.01904   0.01053  -0.0637   0.2715   1.0000
   7.000   1.0229   0.01980   0.01120  -0.0624   0.2396   1.0000
   7.250   1.0414   0.02060   0.01194  -0.0610   0.2092   1.0000
   7.500   1.0592   0.02146   0.01274  -0.0597   0.1808   1.0000
   7.750   1.0760   0.02241   0.01362  -0.0582   0.1522   1.0000
   8.000   1.0916   0.02347   0.01454  -0.0567   0.1212   1.0000
   8.250   1.1055   0.02470   0.01556  -0.0551   0.0894   1.0000
   8.500   1.1196   0.02591   0.01665  -0.0535   0.0649   1.0000
   8.750   1.1329   0.02719   0.01794  -0.0517   0.0482   1.0000
   9.000   1.1429   0.02872   0.01949  -0.0494   0.0366   1.0000
   9.250   1.1488   0.03039   0.02117  -0.0465   0.0306   1.0000
   9.500   1.1564   0.03185   0.02279  -0.0440   0.0269   1.0000
   9.750   1.1614   0.03352   0.02453  -0.0414   0.0241   1.0000
  10.000   1.1667   0.03519   0.02635  -0.0390   0.0223   1.0000
  10.250   1.1726   0.03687   0.02824  -0.0368   0.0206   1.0000
  10.500   1.1768   0.03873   0.03026  -0.0347   0.0195   1.0000
  10.750   1.1803   0.04072   0.03239  -0.0328   0.0188   1.0000
  11.000   1.1824   0.04293   0.03473  -0.0311   0.0182   1.0000
  11.250   1.1834   0.04539   0.03731  -0.0296   0.0177   1.0000
  11.500   1.1850   0.04804   0.04010  -0.0282   0.0173   1.0000
  11.750   1.1880   0.05072   0.04301  -0.0271   0.0169   1.0000
  12.000   1.1899   0.05361   0.04613  -0.0262   0.0167   1.0000
  12.250   1.1898   0.05682   0.04958  -0.0255   0.0164   1.0000
  12.500   1.1878   0.06031   0.05333  -0.0251   0.0162   1.0000
  12.750   1.1828   0.06425   0.05753  -0.0252   0.0160   1.0000
  13.000   1.1755   0.06856   0.06210  -0.0257   0.0159   1.0000
  13.250   1.1655   0.07340   0.06720  -0.0268   0.0158   1.0000
  13.500   1.1534   0.07876   0.07281  -0.0287   0.0157   1.0000
  13.750   1.1391   0.08475   0.07904  -0.0313   0.0157   1.0000
  14.000   1.1229   0.09141   0.08594  -0.0347   0.0157   1.0000
  14.250   1.1051   0.09890   0.09365  -0.0390   0.0158   1.0000
  14.500   1.0857   0.10728   0.10225  -0.0441   0.0159   1.0000
  14.750   1.0653   0.11662   0.11177  -0.0502   0.0161   1.0000
  15.000   1.0434   0.12713   0.12244  -0.0570   0.0164   1.0000
  15.250   1.0213   0.13858   0.13402  -0.0644   0.0166   1.0000
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