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E203 (13.64%) (e203-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E203 (13.64%) (e203-il)
Reynolds number: 200,000
Max Cl/Cd: 78.18 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e203-il-200000.txt
Download as CSV file: xf-e203-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E203  (13.64%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4045   0.07451   0.07124  -0.0587   1.0000   0.0473
 -10.750  -0.3875   0.07594   0.07268  -0.0558   1.0000   0.0483
 -10.500  -0.5304   0.06794   0.06438  -0.0671   1.0000   0.0442
 -10.250  -0.5568   0.06228   0.05868  -0.0701   1.0000   0.0434
 -10.000  -0.5867   0.05802   0.05437  -0.0711   1.0000   0.0429
  -9.750  -0.6176   0.05557   0.05189  -0.0684   1.0000   0.0425
  -9.500  -0.6928   0.04847   0.04425  -0.0628   1.0000   0.0381
  -9.250  -0.7010   0.04681   0.04225  -0.0590   1.0000   0.0361
  -9.000  -0.7110   0.04322   0.03852  -0.0559   1.0000   0.0355
  -8.750  -0.7190   0.04044   0.03551  -0.0527   1.0000   0.0352
  -8.500  -0.6944   0.03576   0.03033  -0.0558   0.9948   0.0347
  -8.250  -0.6643   0.03218   0.02624  -0.0586   0.9887   0.0349
  -8.000  -0.6274   0.03005   0.02364  -0.0617   0.9838   0.0361
  -7.750  -0.5943   0.02796   0.02121  -0.0637   0.9768   0.0365
  -7.500  -0.5596   0.02485   0.01784  -0.0659   0.9725   0.0373
  -7.250  -0.5266   0.02292   0.01584  -0.0676   0.9660   0.0387
  -7.000  -0.4897   0.02155   0.01442  -0.0698   0.9602   0.0405
  -6.750  -0.4522   0.02050   0.01329  -0.0721   0.9544   0.0437
  -6.500  -0.4176   0.01932   0.01200  -0.0737   0.9469   0.0465
  -6.250  -0.3786   0.01783   0.01056  -0.0766   0.9431   0.0516
  -6.000  -0.3481   0.01672   0.00941  -0.0775   0.9333   0.0597
  -5.750  -0.3110   0.01515   0.00808  -0.0800   0.9287   0.1003
  -5.500  -0.2826   0.01407   0.00728  -0.0808   0.9181   0.1654
  -5.250  -0.2494   0.01320   0.00667  -0.0824   0.9103   0.2310
  -5.000  -0.2177   0.01244   0.00623  -0.0835   0.9013   0.3100
  -4.750  -0.1878   0.01211   0.00609  -0.0840   0.8907   0.3832
  -4.500  -0.1550   0.01202   0.00599  -0.0847   0.8815   0.4290
  -4.250  -0.1245   0.01198   0.00586  -0.0850   0.8707   0.4565
  -4.000  -0.0960   0.01198   0.00576  -0.0849   0.8591   0.4779
  -3.750  -0.0673   0.01200   0.00567  -0.0848   0.8484   0.4979
  -3.500  -0.0380   0.01199   0.00558  -0.0848   0.8388   0.5151
  -3.250  -0.0115   0.01201   0.00552  -0.0844   0.8274   0.5299
  -3.000   0.0159   0.01203   0.00544  -0.0841   0.8174   0.5438
  -2.750   0.0442   0.01201   0.00537  -0.0840   0.8087   0.5564
  -2.500   0.0704   0.01201   0.00533  -0.0835   0.7985   0.5680
  -2.250   0.0980   0.01201   0.00526  -0.0834   0.7902   0.5797
  -2.000   0.1253   0.01202   0.00519  -0.0832   0.7813   0.5915
  -1.750   0.1523   0.01203   0.00517  -0.0829   0.7731   0.6024
  -1.500   0.1797   0.01202   0.00512  -0.0827   0.7653   0.6128
  -1.250   0.2067   0.01203   0.00510  -0.0825   0.7575   0.6237
  -1.000   0.2343   0.01204   0.00506  -0.0824   0.7501   0.6348
  -0.750   0.2611   0.01204   0.00508  -0.0821   0.7428   0.6452
  -0.500   0.2884   0.01205   0.00507  -0.0820   0.7357   0.6565
  -0.250   0.3156   0.01208   0.00508  -0.0818   0.7290   0.6686
   0.000   0.3425   0.01209   0.00511  -0.0816   0.7218   0.6807
   0.250   0.3701   0.01211   0.00513  -0.0815   0.7160   0.6930
   0.500   0.3960   0.01212   0.00521  -0.0811   0.7086   0.7064
   0.750   0.4237   0.01213   0.00523  -0.0810   0.7030   0.7213
   1.000   0.4492   0.01216   0.00536  -0.0805   0.6961   0.7380
   1.250   0.4758   0.01218   0.00542  -0.0802   0.6899   0.7572
   1.500   0.5015   0.01221   0.00553  -0.0796   0.6841   0.7784
   1.750   0.5257   0.01222   0.00566  -0.0788   0.6775   0.8044
   2.000   0.5510   0.01223   0.00573  -0.0779   0.6723   0.8343
   2.250   0.5728   0.01224   0.00592  -0.0764   0.6656   0.8711
   2.500   0.6014   0.01223   0.00599  -0.0761   0.6596   0.9159
   2.750   0.6442   0.01230   0.00610  -0.0791   0.6534   0.9603
   3.000   0.6948   0.01235   0.00619  -0.0841   0.6460   0.9978
   3.250   0.7206   0.01251   0.00626  -0.0841   0.6401   1.0000
   3.500   0.7431   0.01267   0.00644  -0.0833   0.6321   1.0000
   3.750   0.7705   0.01281   0.00651  -0.0832   0.6258   1.0000
   4.000   0.7935   0.01295   0.00672  -0.0824   0.6171   1.0000
   4.250   0.8212   0.01308   0.00678  -0.0823   0.6105   1.0000
   4.500   0.8446   0.01321   0.00700  -0.0815   0.6014   1.0000
   4.750   0.8710   0.01333   0.00709  -0.0812   0.5934   1.0000
   5.000   0.8959   0.01341   0.00721  -0.0806   0.5840   1.0000
   5.250   0.9204   0.01352   0.00738  -0.0799   0.5745   1.0000
   5.500   0.9473   0.01359   0.00741  -0.0796   0.5657   1.0000
   5.750   0.9703   0.01367   0.00758  -0.0786   0.5543   1.0000
   6.000   0.9941   0.01374   0.00771  -0.0778   0.5428   1.0000
   6.250   1.0179   0.01381   0.00783  -0.0769   0.5306   1.0000
   6.500   1.0412   0.01387   0.00793  -0.0759   0.5173   1.0000
   6.750   1.0634   0.01395   0.00806  -0.0748   0.5022   1.0000
   7.000   1.0848   0.01405   0.00822  -0.0735   0.4850   1.0000
   7.250   1.1055   0.01419   0.00840  -0.0721   0.4654   1.0000
   7.500   1.1250   0.01439   0.00862  -0.0705   0.4430   1.0000
   7.750   1.1426   0.01467   0.00888  -0.0686   0.4154   1.0000
   8.000   1.1569   0.01511   0.00923  -0.0662   0.3774   1.0000
   8.250   1.1653   0.01584   0.00973  -0.0630   0.3268   1.0000
   8.500   1.1669   0.01694   0.01049  -0.0589   0.2703   1.0000
   8.750   1.1660   0.01813   0.01139  -0.0546   0.2221   1.0000
   9.000   1.1644   0.01937   0.01238  -0.0503   0.1834   1.0000
   9.250   1.1656   0.02061   0.01344  -0.0467   0.1516   1.0000
   9.500   1.1669   0.02193   0.01461  -0.0434   0.1259   1.0000
   9.750   1.1691   0.02329   0.01587  -0.0404   0.1044   1.0000
  10.000   1.1700   0.02483   0.01731  -0.0376   0.0872   1.0000
  10.250   1.1713   0.02646   0.01891  -0.0351   0.0716   1.0000
  10.500   1.1696   0.02844   0.02083  -0.0326   0.0573   1.0000
  10.750   1.1660   0.03071   0.02308  -0.0303   0.0461   1.0000
  11.000   1.1626   0.03312   0.02550  -0.0283   0.0390   1.0000
  11.250   1.1601   0.03558   0.02795  -0.0268   0.0344   1.0000
  11.500   1.1612   0.03786   0.03032  -0.0254   0.0316   1.0000
  11.750   1.1641   0.04004   0.03257  -0.0243   0.0293   1.0000
  12.000   1.1661   0.04236   0.03492  -0.0233   0.0278   1.0000
  12.250   1.1659   0.04504   0.03758  -0.0219   0.0264   1.0000
  12.500   1.1744   0.04694   0.03961  -0.0210   0.0255   1.0000
  12.750   1.1833   0.04887   0.04166  -0.0200   0.0245   1.0000
  13.000   1.1918   0.05089   0.04378  -0.0192   0.0234   1.0000
  13.250   1.2003   0.05293   0.04592  -0.0186   0.0226   1.0000
  13.500   1.2081   0.05504   0.04808  -0.0181   0.0218   1.0000
  13.750   1.2212   0.05723   0.05027  -0.0171   0.0207   1.0000
  14.000   1.2260   0.05999   0.05324  -0.0166   0.0201   1.0000
  14.250   1.2324   0.06272   0.05616  -0.0161   0.0200   1.0000
  14.500   1.2333   0.06590   0.05957  -0.0159   0.0197   1.0000
  14.750   1.2318   0.06952   0.06343  -0.0159   0.0195   1.0000
  15.000   1.2278   0.07344   0.06758  -0.0162   0.0194   1.0000
  15.250   1.2204   0.07791   0.07231  -0.0169   0.0194   1.0000
  15.500   1.2106   0.08273   0.07737  -0.0180   0.0194   1.0000
  15.750   1.1988   0.08801   0.08288  -0.0195   0.0195   1.0000
  16.000   1.1833   0.09398   0.08910  -0.0217   0.0194   1.0000
  16.250   1.1673   0.10031   0.09565  -0.0244   0.0195   1.0000
  16.500   1.1496   0.10721   0.10277  -0.0277   0.0196   1.0000
  16.750   1.1317   0.11451   0.11028  -0.0316   0.0198   1.0000
  17.000   1.1126   0.12238   0.11833  -0.0361   0.0199   1.0000
  17.250   1.0943   0.13056   0.12668  -0.0410   0.0201   1.0000
  17.500   1.0735   0.13978   0.13605  -0.0468   0.0203   1.0000
  17.750   1.0561   0.14876   0.14517  -0.0524   0.0205   1.0000
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