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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 100,000
Max Cl/Cd: 56.53 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e222-il-100000.txt
Download as CSV file: xf-e222-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4179   0.09276   0.08789  -0.0317   1.0000   0.1284
  -8.250  -0.4467   0.09047   0.08578  -0.0347   1.0000   0.1337
  -8.000  -0.4836   0.08700   0.08252  -0.0385   1.0000   0.1351
  -7.750  -0.4420   0.08384   0.07925  -0.0318   1.0000   0.1387
  -7.500  -0.4464   0.08147   0.07695  -0.0302   1.0000   0.1427
  -7.250  -0.5004   0.07668   0.07230  -0.0401   1.0000   0.1493
  -7.000  -0.4805   0.07416   0.06986  -0.0340   1.0000   0.1514
  -6.750  -0.4741   0.07202   0.06775  -0.0310   1.0000   0.1560
  -6.500  -0.4949   0.06708   0.06278  -0.0362   1.0000   0.1649
  -6.250  -0.5074   0.04289   0.03653  -0.0504   1.0000   0.0660
  -6.000  -0.4935   0.03837   0.03190  -0.0502   1.0000   0.0643
  -5.750  -0.4763   0.03501   0.02811  -0.0499   1.0000   0.0640
  -5.500  -0.4564   0.03201   0.02465  -0.0496   1.0000   0.0637
  -5.250  -0.4344   0.02921   0.02141  -0.0492   1.0000   0.0629
  -5.000  -0.4108   0.02687   0.01865  -0.0488   1.0000   0.0625
  -4.750  -0.3864   0.02502   0.01645  -0.0482   1.0000   0.0630
  -4.500  -0.3620   0.02351   0.01464  -0.0475   1.0000   0.0645
  -4.250  -0.3380   0.02218   0.01314  -0.0467   1.0000   0.0666
  -4.000  -0.3155   0.02098   0.01205  -0.0462   1.0000   0.0730
  -3.750  -0.2923   0.02002   0.01105  -0.0455   1.0000   0.0812
  -3.500  -0.2685   0.01893   0.01010  -0.0451   1.0000   0.0975
  -3.250  -0.2412   0.01692   0.00901  -0.0459   1.0000   0.2412
  -3.000  -0.2190   0.01643   0.00902  -0.0457   1.0000   0.3587
  -2.750  -0.1984   0.01624   0.00919  -0.0450   1.0000   0.4565
  -2.500  -0.1794   0.01615   0.00940  -0.0436   1.0000   0.5352
  -2.250  -0.1614   0.01616   0.00958  -0.0419   1.0000   0.6016
  -2.000  -0.1425   0.01624   0.00983  -0.0403   0.9991   0.6657
  -1.750  -0.1070   0.01654   0.01027  -0.0414   0.9901   0.7381
  -1.500  -0.0750   0.01680   0.01061  -0.0416   0.9809   0.8058
  -1.250  -0.0449   0.01696   0.01085  -0.0411   0.9714   0.8790
  -1.000   0.0079   0.01678   0.01062  -0.0459   0.9616   1.0000
  -0.750   0.0546   0.01699   0.01054  -0.0509   0.9521   1.0000
  -0.500   0.1052   0.01723   0.01057  -0.0561   0.9443   1.0000
  -0.250   0.1449   0.01736   0.01054  -0.0590   0.9329   1.0000
   0.000   0.1856   0.01750   0.01053  -0.0619   0.9222   1.0000
   0.250   0.2325   0.01758   0.01050  -0.0658   0.9139   1.0000
   0.500   0.2741   0.01759   0.01043  -0.0686   0.9033   1.0000
   0.750   0.3124   0.01760   0.01038  -0.0706   0.8918   1.0000
   1.000   0.3554   0.01750   0.01024  -0.0733   0.8819   1.0000
   1.250   0.4048   0.01723   0.00995  -0.0770   0.8739   1.0000
   1.500   0.4431   0.01708   0.00979  -0.0787   0.8621   1.0000
   1.750   0.4826   0.01686   0.00958  -0.0804   0.8508   1.0000
   2.000   0.5260   0.01650   0.00924  -0.0826   0.8408   1.0000
   2.250   0.5666   0.01615   0.00891  -0.0841   0.8293   1.0000
   2.500   0.6013   0.01593   0.00873  -0.0847   0.8151   1.0000
   2.750   0.6355   0.01570   0.00852  -0.0851   0.8002   1.0000
   3.000   0.6661   0.01558   0.00842  -0.0849   0.7831   1.0000
   3.250   0.6947   0.01552   0.00838  -0.0843   0.7644   1.0000
   3.500   0.7249   0.01543   0.00832  -0.0840   0.7456   1.0000
   3.750   0.7559   0.01535   0.00821  -0.0837   0.7268   1.0000
   4.000   0.7808   0.01545   0.00833  -0.0826   0.7037   1.0000
   4.250   0.8088   0.01548   0.00836  -0.0819   0.6815   1.0000
   4.500   0.8340   0.01561   0.00848  -0.0808   0.6566   1.0000
   4.750   0.8585   0.01577   0.00863  -0.0796   0.6304   1.0000
   5.000   0.8828   0.01596   0.00880  -0.0784   0.6032   1.0000
   5.250   0.9063   0.01620   0.00902  -0.0770   0.5744   1.0000
   5.500   0.9289   0.01648   0.00927  -0.0756   0.5439   1.0000
   5.750   0.9508   0.01682   0.00954  -0.0741   0.5119   1.0000
   6.000   0.9720   0.01722   0.00985  -0.0725   0.4789   1.0000
   6.250   0.9914   0.01768   0.01030  -0.0708   0.4424   1.0000
   6.500   1.0103   0.01823   0.01072  -0.0689   0.4058   1.0000
   6.750   1.0277   0.01886   0.01128  -0.0670   0.3661   1.0000
   7.000   1.0441   0.01961   0.01191  -0.0650   0.3255   1.0000
   7.250   1.0594   0.02051   0.01265  -0.0629   0.2855   1.0000
   7.500   1.0736   0.02159   0.01353  -0.0608   0.2470   1.0000
   7.750   1.0873   0.02274   0.01457  -0.0586   0.2089   1.0000
   8.000   1.0989   0.02397   0.01561  -0.0563   0.1738   1.0000
   8.250   1.1093   0.02509   0.01661  -0.0541   0.1387   1.0000
   8.500   1.1178   0.02666   0.01799  -0.0516   0.1089   1.0000
   8.750   1.1235   0.02872   0.01986  -0.0487   0.0811   1.0000
   9.000   1.1324   0.03096   0.02209  -0.0459   0.0634   1.0000
   9.250   1.1477   0.03346   0.02453  -0.0443   0.0553   1.0000
   9.500   1.1648   0.03540   0.02658  -0.0429   0.0494   1.0000
   9.750   1.1859   0.03821   0.02946  -0.0423   0.0451   1.0000
  10.000   1.2055   0.04076   0.03231  -0.0412   0.0426   1.0000
  10.250   1.2235   0.04369   0.03553  -0.0400   0.0410   1.0000
  10.500   1.2367   0.04677   0.03893  -0.0385   0.0400   1.0000
  10.750   1.2445   0.05008   0.04257  -0.0365   0.0395   1.0000
  11.000   1.2458   0.05349   0.04635  -0.0340   0.0394   1.0000
  11.250   1.2375   0.05693   0.05018  -0.0306   0.0395   1.0000
  11.500   1.2224   0.06054   0.05418  -0.0273   0.0399   1.0000
  11.750   1.2033   0.06449   0.05848  -0.0246   0.0403   1.0000
  12.000   1.1813   0.06892   0.06324  -0.0230   0.0407   1.0000
  12.250   1.1576   0.07388   0.06849  -0.0227   0.0412   1.0000
  12.500   1.1319   0.07955   0.07441  -0.0238   0.0417   1.0000
  12.750   1.1051   0.08602   0.08111  -0.0263   0.0422   1.0000
  13.000   1.0770   0.09355   0.08885  -0.0305   0.0427   1.0000
  13.250   1.0473   0.10248   0.09794  -0.0363   0.0434   1.0000
  13.500   1.0175   0.11292   0.10849  -0.0435   0.0442   1.0000
  13.750   0.9917   0.12405   0.11966  -0.0508   0.0452   1.0000
  14.000   0.9778   0.13316   0.12877  -0.0557   0.0462   1.0000
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