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E222 (10.17%) (e222-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E222 (10.17%) (e222-il)
Reynolds number: 50,000
Max Cl/Cd: 36.53 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e222-il-50000.txt
Download as CSV file: xf-e222-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4035   0.10639   0.09940  -0.0208   1.0000   0.2635
  -8.500  -0.3945   0.10244   0.09549  -0.0202   1.0000   0.2697
  -8.250  -0.4153   0.10191   0.09512  -0.0202   1.0000   0.2795
  -8.000  -0.3908   0.09684   0.08999  -0.0188   1.0000   0.2894
  -7.750  -0.3908   0.09405   0.08729  -0.0179   1.0000   0.2995
  -7.500  -0.4197   0.09388   0.08733  -0.0168   1.0000   0.3091
  -7.250  -0.3976   0.08936   0.08279  -0.0154   1.0000   0.3213
  -7.000  -0.3952   0.08619   0.07970  -0.0140   1.0000   0.3289
  -6.500  -0.4994   0.06173   0.05510  -0.0463   1.0000   0.1353
  -6.250  -0.4970   0.05459   0.04738  -0.0495   1.0000   0.1206
  -6.000  -0.4839   0.05079   0.04357  -0.0486   1.0000   0.1178
  -5.750  -0.4712   0.04638   0.03883  -0.0491   1.0000   0.1150
  -5.500  -0.4552   0.04223   0.03419  -0.0498   1.0000   0.1142
  -5.250  -0.4357   0.03865   0.03008  -0.0502   1.0000   0.1153
  -5.000  -0.4135   0.03543   0.02631  -0.0503   1.0000   0.1165
  -4.750  -0.3893   0.03259   0.02287  -0.0502   1.0000   0.1182
  -4.500  -0.3646   0.03011   0.01996  -0.0497   1.0000   0.1221
  -4.250  -0.3411   0.02832   0.01804  -0.0489   1.0000   0.1314
  -4.000  -0.3169   0.02669   0.01620  -0.0481   1.0000   0.1487
  -3.750  -0.2932   0.02488   0.01465  -0.0471   1.0000   0.1806
  -3.500  -0.2710   0.02316   0.01360  -0.0464   1.0000   0.2850
  -3.250  -0.2523   0.02212   0.01329  -0.0445   1.0000   0.4157
  -3.000  -0.2357   0.02161   0.01319  -0.0416   1.0000   0.5166
  -2.750  -0.2225   0.02134   0.01325  -0.0376   1.0000   0.5970
  -2.500  -0.2119   0.02113   0.01325  -0.0330   1.0000   0.6700
  -2.250  -0.2048   0.02095   0.01319  -0.0277   1.0000   0.7389
  -2.000  -0.2030   0.02070   0.01309  -0.0213   1.0000   0.8055
  -1.750  -0.1999   0.02027   0.01279  -0.0150   1.0000   0.8904
  -1.500  -0.1392   0.01964   0.01177  -0.0235   1.0000   1.0000
  -1.250  -0.1126   0.01960   0.01127  -0.0265   1.0000   1.0000
  -1.000  -0.0868   0.01982   0.01113  -0.0282   1.0000   1.0000
  -0.750  -0.0628   0.02014   0.01115  -0.0293   1.0000   1.0000
  -0.500  -0.0400   0.02054   0.01129  -0.0300   1.0000   1.0000
  -0.250  -0.0182   0.02099   0.01150  -0.0305   1.0000   1.0000
   0.000   0.0030   0.02150   0.01182  -0.0308   1.0000   1.0000
   0.250   0.0236   0.02207   0.01221  -0.0312   1.0000   1.0000
   0.500   0.0436   0.02269   0.01269  -0.0314   1.0000   1.0000
   0.750   0.0631   0.02337   0.01324  -0.0317   1.0000   1.0000
   1.000   0.0822   0.02410   0.01386  -0.0320   1.0000   1.0000
   1.250   0.1184   0.02526   0.01491  -0.0355   0.9917   1.0000
   1.500   0.1692   0.02662   0.01619  -0.0414   0.9749   1.0000
   1.750   0.2199   0.02789   0.01739  -0.0471   0.9583   1.0000
   2.000   0.2629   0.02887   0.01834  -0.0512   0.9405   1.0000
   2.250   0.3057   0.02978   0.01925  -0.0551   0.9223   1.0000
   2.500   0.3506   0.03064   0.02013  -0.0590   0.9046   1.0000
   2.750   0.3988   0.03140   0.02094  -0.0632   0.8871   1.0000
   3.000   0.4326   0.03206   0.02167  -0.0649   0.8674   1.0000
   3.250   0.4736   0.03261   0.02230  -0.0675   0.8481   1.0000
   3.500   0.5212   0.03295   0.02279  -0.0706   0.8300   1.0000
   3.750   0.5561   0.03338   0.02334  -0.0718   0.8096   1.0000
   4.000   0.5981   0.03351   0.02363  -0.0736   0.7897   1.0000
   4.250   0.6542   0.03296   0.02333  -0.0765   0.7715   1.0000
   4.500   0.6888   0.03301   0.02355  -0.0767   0.7494   1.0000
   4.750   0.7409   0.03209   0.02287  -0.0782   0.7295   1.0000
   5.000   0.7803   0.03156   0.02259  -0.0780   0.7066   1.0000
   5.250   0.8333   0.03011   0.02137  -0.0786   0.6839   1.0000
   5.500   0.8688   0.02950   0.02093  -0.0775   0.6565   1.0000
   5.750   0.9063   0.02871   0.02032  -0.0763   0.6269   1.0000
   6.000   0.9412   0.02809   0.01977  -0.0748   0.5946   1.0000
   6.250   0.9662   0.02806   0.01982  -0.0725   0.5585   1.0000
   6.500   0.9946   0.02787   0.01962  -0.0704   0.5199   1.0000
   6.750   1.0197   0.02797   0.01960  -0.0681   0.4788   1.0000
   7.000   1.0396   0.02846   0.01998  -0.0655   0.4356   1.0000
   7.250   1.0584   0.02918   0.02051  -0.0629   0.3913   1.0000
   7.500   1.0744   0.03019   0.02134  -0.0602   0.3471   1.0000
   7.750   1.0902   0.03145   0.02241  -0.0577   0.3044   1.0000
   8.000   1.1033   0.03304   0.02392  -0.0550   0.2650   1.0000
   8.250   1.1182   0.03492   0.02565  -0.0527   0.2288   1.0000
   8.500   1.1314   0.03696   0.02759  -0.0503   0.1953   1.0000
   8.750   1.1435   0.03904   0.02943  -0.0480   0.1639   1.0000
   9.000   1.1520   0.04129   0.03165  -0.0454   0.1375   1.0000
   9.250   1.1635   0.04421   0.03464  -0.0433   0.1179   1.0000
   9.500   1.1771   0.04751   0.03815  -0.0415   0.1050   1.0000
   9.750   1.1929   0.05092   0.04173  -0.0401   0.0965   1.0000
  10.000   1.1964   0.05486   0.04615  -0.0376   0.0922   1.0000
  10.250   1.1941   0.05857   0.05037  -0.0348   0.0888   1.0000
  10.500   1.1937   0.06227   0.05438  -0.0325   0.0862   1.0000
  10.750   1.1922   0.06627   0.05864  -0.0305   0.0846   1.0000
  11.000   1.1743   0.07035   0.06310  -0.0275   0.0849   1.0000
  11.250   1.1448   0.07462   0.06772  -0.0247   0.0859   1.0000
  11.500   1.1119   0.07969   0.07308  -0.0237   0.0875   1.0000
  11.750   1.0790   0.08584   0.07945  -0.0248   0.0895   1.0000
  12.000   1.0498   0.09285   0.08660  -0.0276   0.0914   1.0000
  12.250   1.0261   0.10041   0.09423  -0.0312   0.0932   1.0000
  12.500   1.0082   0.10817   0.10204  -0.0351   0.0943   1.0000
  12.750   0.8643   0.15459   0.14802  -0.0741   0.2093   1.0000
  13.000   0.8735   0.15766   0.15111  -0.0733   0.1871   1.0000
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