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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 500,000
Max Cl/Cd: 98.86 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e205-il-500000-n5.txt
Download as CSV file: xf-e205-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E205  (10.48%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5567   0.04953   0.04735  -0.0505   1.0000   0.0095
  -8.750  -0.5863   0.04025   0.03764  -0.0521   1.0000   0.0094
  -8.500  -0.5863   0.03278   0.02957  -0.0552   0.9877   0.0095
  -8.250  -0.5698   0.02840   0.02474  -0.0569   0.9757   0.0097
  -8.000  -0.5472   0.02570   0.02171  -0.0581   0.9611   0.0099
  -7.750  -0.5204   0.02346   0.01916  -0.0594   0.9417   0.0101
  -7.500  -0.4926   0.02182   0.01724  -0.0603   0.9139   0.0104
  -7.250  -0.4698   0.02054   0.01566  -0.0598   0.8814   0.0106
  -7.000  -0.4491   0.01941   0.01419  -0.0587   0.8504   0.0109
  -6.750  -0.4280   0.01834   0.01282  -0.0575   0.8235   0.0110
  -6.500  -0.4060   0.01739   0.01160  -0.0565   0.7997   0.0113
  -6.250  -0.3831   0.01653   0.01050  -0.0557   0.7785   0.0115
  -6.000  -0.3594   0.01582   0.00958  -0.0549   0.7591   0.0118
  -5.750  -0.3351   0.01522   0.00879  -0.0543   0.7417   0.0123
  -5.500  -0.3107   0.01457   0.00794  -0.0536   0.7259   0.0126
  -5.250  -0.2861   0.01393   0.00714  -0.0530   0.7112   0.0128
  -4.750  -0.2361   0.01285   0.00578  -0.0518   0.6854   0.0132
  -4.500  -0.2106   0.01243   0.00525  -0.0513   0.6737   0.0135
  -4.250  -0.1848   0.01207   0.00477  -0.0508   0.6630   0.0137
  -4.000  -0.1599   0.01151   0.00409  -0.0502   0.6531   0.0143
  -3.750  -0.1341   0.01113   0.00362  -0.0498   0.6432   0.0150
  -3.500  -0.1077   0.01086   0.00327  -0.0495   0.6344   0.0157
  -3.250  -0.0812   0.01065   0.00297  -0.0491   0.6259   0.0164
  -3.000  -0.0543   0.01046   0.00271  -0.0489   0.6175   0.0174
  -2.750  -0.0275   0.01031   0.00247  -0.0486   0.6099   0.0189
  -2.500  -0.0004   0.01014   0.00226  -0.0484   0.6024   0.0209
  -2.250   0.0262   0.00994   0.00207  -0.0481   0.5954   0.0320
  -2.000   0.0527   0.00969   0.00191  -0.0478   0.5883   0.0636
  -1.750   0.0790   0.00947   0.00179  -0.0476   0.5819   0.1017
  -1.500   0.1058   0.00926   0.00170  -0.0474   0.5754   0.1419
  -1.250   0.1321   0.00906   0.00162  -0.0472   0.5690   0.1897
  -1.000   0.1579   0.00873   0.00156  -0.0469   0.5632   0.2761
  -0.750   0.1826   0.00832   0.00152  -0.0465   0.5572   0.3942
  -0.500   0.2076   0.00802   0.00150  -0.0460   0.5516   0.4913
  -0.250   0.2314   0.00764   0.00149  -0.0453   0.5458   0.6081
   0.000   0.2542   0.00731   0.00150  -0.0441   0.5404   0.7171
   0.250   0.2766   0.00698   0.00154  -0.0426   0.5352   0.8300
   0.500   0.3252   0.00693   0.00166  -0.0466   0.5286   0.9366
   0.750   0.3638   0.00702   0.00169  -0.0488   0.5231   0.9626
   1.000   0.3992   0.00710   0.00173  -0.0504   0.5169   0.9757
   1.250   0.4359   0.00719   0.00175  -0.0523   0.5112   0.9850
   1.500   0.4758   0.00724   0.00177  -0.0549   0.5053   0.9915
   1.750   0.5151   0.00730   0.00178  -0.0575   0.4990   0.9968
   2.000   0.5512   0.00736   0.00181  -0.0593   0.4933   1.0000
   2.250   0.5763   0.00742   0.00185  -0.0588   0.4872   1.0000
   2.500   0.6012   0.00752   0.00191  -0.0582   0.4815   1.0000
   2.750   0.6264   0.00758   0.00197  -0.0576   0.4747   1.0000
   3.000   0.6512   0.00769   0.00204  -0.0570   0.4677   1.0000
   3.250   0.6763   0.00777   0.00212  -0.0564   0.4594   1.0000
   3.500   0.7011   0.00788   0.00221  -0.0558   0.4514   1.0000
   3.750   0.7260   0.00799   0.00231  -0.0552   0.4424   1.0000
   4.000   0.7508   0.00810   0.00241  -0.0546   0.4333   1.0000
   4.250   0.7754   0.00824   0.00252  -0.0540   0.4237   1.0000
   4.500   0.8000   0.00837   0.00266  -0.0534   0.4131   1.0000
   4.750   0.8246   0.00851   0.00280  -0.0527   0.4022   1.0000
   5.000   0.8489   0.00868   0.00295  -0.0521   0.3899   1.0000
   5.250   0.8728   0.00887   0.00311  -0.0514   0.3753   1.0000
   5.500   0.8967   0.00907   0.00329  -0.0506   0.3605   1.0000
   5.750   0.9200   0.00932   0.00351  -0.0498   0.3425   1.0000
   6.000   0.9425   0.00962   0.00374  -0.0489   0.3181   1.0000
   6.250   0.9619   0.01018   0.00408  -0.0476   0.2727   1.0000
   6.500   0.9787   0.01098   0.00457  -0.0460   0.2157   1.0000
   6.750   0.9954   0.01178   0.00511  -0.0443   0.1660   1.0000
   7.000   1.0138   0.01244   0.00562  -0.0429   0.1327   1.0000
   7.250   1.0331   0.01302   0.00608  -0.0417   0.1085   1.0000
   7.500   1.0525   0.01358   0.00656  -0.0404   0.0876   1.0000
   7.750   1.0710   0.01420   0.00708  -0.0391   0.0679   1.0000
   8.000   1.0894   0.01481   0.00761  -0.0377   0.0510   1.0000
   8.250   1.1062   0.01552   0.00824  -0.0362   0.0343   1.0000
   8.500   1.1215   0.01632   0.00895  -0.0344   0.0185   1.0000
   8.750   1.1365   0.01710   0.00968  -0.0326   0.0098   1.0000
   9.000   1.1532   0.01773   0.01034  -0.0310   0.0081   1.0000
   9.250   1.1686   0.01841   0.01107  -0.0293   0.0070   1.0000
   9.500   1.1847   0.01899   0.01173  -0.0276   0.0067   1.0000
   9.750   1.1985   0.01963   0.01246  -0.0256   0.0063   1.0000
  10.000   1.2092   0.02030   0.01322  -0.0232   0.0061   1.0000
  10.250   1.2180   0.02109   0.01410  -0.0205   0.0058   1.0000
  10.500   1.2270   0.02192   0.01501  -0.0182   0.0057   1.0000
  10.750   1.2341   0.02292   0.01610  -0.0158   0.0054   1.0000
  11.000   1.2410   0.02402   0.01728  -0.0137   0.0052   1.0000
  11.250   1.2464   0.02530   0.01866  -0.0118   0.0051   1.0000
  11.500   1.2484   0.02696   0.02041  -0.0100   0.0047   1.0000
  11.750   1.2517   0.02867   0.02221  -0.0086   0.0047   1.0000
  12.000   1.2491   0.03103   0.02470  -0.0073   0.0044   1.0000
  12.250   1.2474   0.03350   0.02727  -0.0064   0.0043   1.0000
  12.500   1.2520   0.03547   0.02935  -0.0059   0.0043   1.0000
  12.750   1.2538   0.03781   0.03181  -0.0055   0.0042   1.0000
  13.000   1.2558   0.04022   0.03431  -0.0052   0.0042   1.0000
  13.250   1.2556   0.04291   0.03712  -0.0051   0.0041   1.0000
  13.500   1.2548   0.04575   0.04006  -0.0051   0.0041   1.0000
  13.750   1.2540   0.04864   0.04306  -0.0052   0.0040   1.0000
  14.000   1.2526   0.05166   0.04619  -0.0055   0.0040   1.0000
  14.250   1.2501   0.05491   0.04955  -0.0059   0.0040   1.0000
  14.500   1.2464   0.05838   0.05313  -0.0065   0.0039   1.0000
  14.750   1.2434   0.06190   0.05677  -0.0072   0.0039   1.0000
  15.000   1.2398   0.06562   0.06060  -0.0081   0.0039   1.0000
  15.250   1.2363   0.06943   0.06452  -0.0091   0.0038   1.0000
  15.500   1.2321   0.07348   0.06870  -0.0104   0.0037   1.0000
  15.750   1.2261   0.07791   0.07324  -0.0118   0.0037   1.0000
  16.000   1.2212   0.08230   0.07775  -0.0133   0.0037   1.0000
  16.250   1.2160   0.08685   0.08243  -0.0151   0.0036   1.0000
  16.500   1.2084   0.09194   0.08765  -0.0171   0.0036   1.0000
  16.750   1.2020   0.09696   0.09279  -0.0192   0.0036   1.0000
  17.000   1.1941   0.10239   0.09837  -0.0217   0.0035   1.0000
  17.250   1.1863   0.10790   0.10400  -0.0242   0.0036   1.0000
  17.500   1.1784   0.11364   0.10987  -0.0270   0.0035   1.0000
  17.750   1.1698   0.11958   0.11593  -0.0300   0.0035   1.0000
  18.000   1.1603   0.12593   0.12241  -0.0333   0.0035   1.0000
  18.250   1.1511   0.13230   0.12891  -0.0368   0.0034   1.0000
  18.500   1.1414   0.13896   0.13570  -0.0404   0.0035   1.0000
  18.750   1.1313   0.14585   0.14272  -0.0443   0.0035   1.0000
  19.000   1.1206   0.15311   0.15010  -0.0485   0.0035   1.0000
  19.250   1.1108   0.16034   0.15746  -0.0528   0.0035   1.0000
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