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E214 (11.1%) (e214-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E214 (11.1%) (e214-il)
Reynolds number: 100,000
Max Cl/Cd: 61.9 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e214-il-100000.txt
Download as CSV file: xf-e214-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E214  (11.1%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2911   0.10601   0.10175  -0.0321   1.0000   0.0981
  -8.750  -0.3119   0.10450   0.10033  -0.0329   1.0000   0.0998
  -8.500  -0.3358   0.10314   0.09908  -0.0335   1.0000   0.1004
  -8.250  -0.3087   0.09800   0.09393  -0.0293   1.0000   0.1041
  -8.000  -0.3092   0.09587   0.09184  -0.0274   1.0000   0.1082
  -7.750  -0.3219   0.09390   0.08995  -0.0266   1.0000   0.1119
  -7.500  -0.3885   0.09643   0.09213  -0.0290   1.0000   0.1053
  -7.250  -0.3964   0.09470   0.09047  -0.0268   1.0000   0.1085
  -7.000  -0.4153   0.09338   0.08926  -0.0245   1.0000   0.1110
  -6.750  -0.4346   0.09165   0.08764  -0.0238   1.0000   0.1124
  -6.500  -0.4612   0.08788   0.08395  -0.0336   1.0000   0.1145
  -6.250  -0.4592   0.08498   0.08113  -0.0278   1.0000   0.1169
  -6.000  -0.4541   0.08373   0.07992  -0.0224   1.0000   0.1216
  -5.750  -0.4647   0.07674   0.07270  -0.0414   1.0000   0.1297
  -5.500  -0.4604   0.07544   0.07165  -0.0311   1.0000   0.1322
  -5.250  -0.4562   0.07361   0.06985  -0.0285   1.0000   0.1366
  -5.000  -0.4123   0.06527   0.06108  -0.0493   0.9923   0.1595
  -4.750  -0.3898   0.06265   0.05862  -0.0468   0.9868   0.1639
  -4.500  -0.3495   0.05737   0.05305  -0.0577   0.9794   0.1899
  -4.250  -0.2840   0.04472   0.03933  -0.0741   0.9761   0.1326
  -4.000  -0.2143   0.03398   0.02633  -0.0823   0.9753   0.0730
  -3.750  -0.1688   0.03134   0.02319  -0.0860   0.9714   0.0721
  -3.500  -0.1319   0.02947   0.02090  -0.0879   0.9642   0.0724
  -3.250  -0.0898   0.02755   0.01888  -0.0910   0.9599   0.0772
  -3.000  -0.0550   0.02660   0.01778  -0.0925   0.9521   0.0835
  -2.750  -0.0131   0.02538   0.01657  -0.0950   0.9472   0.0911
  -2.500   0.0213   0.02450   0.01578  -0.0965   0.9394   0.1081
  -2.250   0.0655   0.02233   0.01472  -0.1005   0.9350   0.2935
  -2.000   0.0955   0.02182   0.01536  -0.1007   0.9277   0.5975
  -1.500   0.1492   0.02212   0.01577  -0.0985   0.9104   0.7349
  -1.250   0.1825   0.02209   0.01571  -0.0984   0.9045   0.7820
  -1.000   0.2003   0.02207   0.01569  -0.0959   0.8938   0.8181
  -0.750   0.2232   0.02195   0.01553  -0.0942   0.8854   0.8575
  -0.500   0.2470   0.02164   0.01522  -0.0924   0.8776   0.9022
  -0.250   0.2851   0.02134   0.01490  -0.0945   0.8682   1.0000
   0.000   0.3372   0.02123   0.01456  -0.0999   0.8629   1.0000
   0.250   0.3750   0.02136   0.01452  -0.1028   0.8536   1.0000
   0.500   0.4245   0.02115   0.01415  -0.1071   0.8486   1.0000
   0.750   0.4584   0.02127   0.01415  -0.1088   0.8389   1.0000
   1.000   0.5071   0.02090   0.01366  -0.1125   0.8344   1.0000
   1.250   0.5393   0.02099   0.01366  -0.1136   0.8248   1.0000
   1.500   0.5882   0.02054   0.01314  -0.1171   0.8202   1.0000
   1.750   0.6209   0.02057   0.01312  -0.1180   0.8107   1.0000
   2.000   0.6681   0.02011   0.01262  -0.1211   0.8055   1.0000
   2.250   0.6989   0.02015   0.01264  -0.1216   0.7954   1.0000
   2.500   0.7467   0.01960   0.01207  -0.1246   0.7902   1.0000
   2.750   0.7754   0.01969   0.01217  -0.1247   0.7789   1.0000
   3.000   0.8115   0.01954   0.01202  -0.1258   0.7699   1.0000
   3.250   0.8521   0.01922   0.01169  -0.1276   0.7616   1.0000
   3.500   0.8810   0.01930   0.01182  -0.1276   0.7497   1.0000
   3.750   0.9127   0.01930   0.01184  -0.1279   0.7383   1.0000
   4.000   0.9478   0.01919   0.01173  -0.1288   0.7274   1.0000
   4.250   0.9848   0.01901   0.01158  -0.1299   0.7163   1.0000
   4.500   1.0125   0.01914   0.01174  -0.1295   0.7027   1.0000
   4.750   1.0405   0.01926   0.01189  -0.1292   0.6886   1.0000
   5.000   1.0686   0.01937   0.01205  -0.1288   0.6742   1.0000
   5.250   1.0966   0.01946   0.01218  -0.1284   0.6592   1.0000
   5.500   1.1246   0.01954   0.01228  -0.1279   0.6436   1.0000
   5.750   1.1494   0.01970   0.01248  -0.1269   0.6266   1.0000
   6.000   1.1723   0.01989   0.01276  -0.1256   0.6087   1.0000
   6.250   1.1962   0.02004   0.01296  -0.1245   0.5903   1.0000
   6.500   1.2214   0.02014   0.01307  -0.1235   0.5714   1.0000
   6.750   1.2421   0.02033   0.01332  -0.1218   0.5505   1.0000
   7.000   1.2631   0.02049   0.01353  -0.1201   0.5283   1.0000
   7.250   1.2813   0.02073   0.01382  -0.1179   0.5045   1.0000
   7.500   1.2992   0.02099   0.01408  -0.1158   0.4792   1.0000
   7.750   1.3144   0.02133   0.01442  -0.1132   0.4515   1.0000
   8.000   1.3265   0.02178   0.01487  -0.1102   0.4207   1.0000
   8.250   1.3361   0.02235   0.01544  -0.1068   0.3869   1.0000
   8.500   1.3428   0.02310   0.01606  -0.1031   0.3512   1.0000
   8.750   1.3460   0.02403   0.01688  -0.0989   0.3132   1.0000
   9.000   1.3457   0.02521   0.01784  -0.0944   0.2772   1.0000
   9.250   1.3448   0.02661   0.01907  -0.0901   0.2416   1.0000
   9.500   1.3433   0.02826   0.02050  -0.0861   0.2105   1.0000
   9.750   1.3424   0.03005   0.02212  -0.0823   0.1829   1.0000
  10.000   1.3426   0.03197   0.02390  -0.0790   0.1594   1.0000
  10.250   1.3433   0.03398   0.02577  -0.0760   0.1399   1.0000
  10.500   1.3457   0.03610   0.02778  -0.0733   0.1226   1.0000
  10.750   1.3487   0.03821   0.02993  -0.0708   0.1073   1.0000
  11.000   1.3513   0.04042   0.03213  -0.0685   0.0940   1.0000
  11.250   1.3537   0.04274   0.03444  -0.0664   0.0823   1.0000
  11.500   1.3580   0.04521   0.03684  -0.0647   0.0718   1.0000
  11.750   1.3603   0.04758   0.03935  -0.0628   0.0635   1.0000
  12.000   1.3675   0.05036   0.04226  -0.0612   0.0558   1.0000
  12.250   1.3879   0.05349   0.04528  -0.0605   0.0491   1.0000
  12.500   1.3915   0.05626   0.04843  -0.0588   0.0458   1.0000
  12.750   1.3942   0.05900   0.05136  -0.0574   0.0427   1.0000
  13.000   1.4151   0.06320   0.05556  -0.0573   0.0392   1.0000
  13.250   1.4098   0.06675   0.05950  -0.0556   0.0386   1.0000
  13.500   1.4023   0.07078   0.06390  -0.0543   0.0381   1.0000
  13.750   1.3914   0.07521   0.06869  -0.0533   0.0377   1.0000
  14.000   1.3775   0.08003   0.07384  -0.0529   0.0375   1.0000
  14.250   1.3611   0.08525   0.07939  -0.0531   0.0374   1.0000
  14.500   1.3426   0.09089   0.08532  -0.0539   0.0374   1.0000
  14.750   1.3226   0.09696   0.09167  -0.0556   0.0375   1.0000
  15.000   1.3015   0.10352   0.09849  -0.0580   0.0377   1.0000
  15.250   1.2798   0.11060   0.10579  -0.0612   0.0379   1.0000
  15.500   1.2580   0.11820   0.11360  -0.0653   0.0382   1.0000
  15.750   1.2361   0.12642   0.12200  -0.0701   0.0385   1.0000
  16.000   1.2151   0.13516   0.13089  -0.0756   0.0389   1.0000
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